Popular technology article
Dynamic symmetry is a novel concept in the design and
fabrication of gas turbines, breaking away from today’s paradigm in the
engineering of this kind of engines. Since the compressor and hot gas
turbine are both turbo-machines sharing many features and working under
the same physical phenomena, the dynamic symmetry concept seeks to
combine the expansion and compression functions in a unique rotor
element, therefore reducing its structural requirements to the bare
minimum whilst achieving an excellent cooling scheme.
is considered a theoretical dynamic symmetry surface (1), one that has a
warped shape in such a manner that it allows to conduct a fluid current
(2) over one of its sides describing a given path and exerting some
given efforts on it, while at the same time allows to conduct another
fluid current (3) over its other side describing another path
symmetrical to the first one and exerting some efforts symmetrical to
the first ones on it.
Albeit the rule defining this criterion remains relatively simple, the
reality is that the general concept remains unintuitive and results
difficult to completely understand without the help of drawings because
its application generates three-dimensional unconventional geometries.
Despite this, once understood, this new technique translates into the
design of simple architectures which have resulted being naturally
functional and versatile. A detailed description of this technology is
The dynamic symmetry strategy is specifically used in the design of the
turbine rotors, be it for axial, radial or mixed flow. When constructed,
the particularities of these rotors have a significant impact on the
overall conception of turbo-machines into which they are integrated,
leading to their structures also being unconventional. Dynamic symmetry
foils rotor are simply made by joining two types of foils, one being a
pressure foil (active surface) and the other being a suction foil
(passive surface), whose unconventional shapes are derived from the
dynamic symmetry criterion. Due to this technique, the rotor works
simultaneously as a pump and motor, substantially reducing the need for
structural materials in its fabrication. Any surface of the rotor is in
contact with the expanding fluid on one of its sides whilst also being
in contact with the compressing fluid on the other.
One of the foil types performs the function of active surface for the
compression on one of its sides and expansion on the other. Similarly,
the other type of foil performs the function of a passive surface for
compression on one of its sides and expansion on the other one.
Figure 1 shows a dynamic symmetry active surface 1 in which the paths of
the expanding flow 2 and the compressing flow 3, represented by arrow
tiers, can also be seen. Notice how said curved paths induce the
creation of a pressure differential between the surface and the fluid.
It can be observed in this theoretical example how the geometry and the
paths exhibit symmetry with respect to an imaginary straight line
passing through the two opposed vertex of the surface.
Figure 2 shows a dynamic symmetry passive surface 4 in which the paths
of the expanding flow 2 and the compressing flow 3, represented by arrow
tiers, can also be seen. Notice how said curved paths induce the
apparition of a suction force between the surface and the fluid. As what
happens with classical axial flow blades, the dynamic symmetry passive
surface has a more pronounced curvature than that of the active surface.
Due to the special geometrical characteristics in a dynamic symmetry
foils rotor, it is not possible to consider the classic concept of blade
as a constructive element. The rotor is built by adequately joining a
series of foils where the active with the passive ones alternate in such
a way that two types of equally alternative channels are formed, one
assigned to conducting the compressing fluid whilst the other, adjacent
to the first, assigned to conducting the expanding fluid.
Figure 3 shows the joining of a dynamic symmetry passive surface 4 and
two dynamic symmetry active surfaces 1. This view demonstrates how the
passages are formed through which both the expanding flow 2 and the
compressing flow 3 must circulate.
Notice how the passive surface 4 is joined by two boundaries with one of
its adjacent active surface 1, while the other two join the other
active surface 1. The same happens in a reciprocal way for the active
surfaces with respect to the passive ones. As can be seen in this
example, the dynamic symmetry active surface will have all of its
boundaries joined to a passive surface; however, the same does not hold
for the dynamic symmetry passive surface which will have some
unconnected edges. Although it is perfectly reasonable to conceive both
or only the active surface with the previously described free edges, the
main reason for this setup is merely a geometric convenience.
Nonetheless, such a design would generate strained geometries.
The fact that a passage ends up being one of compression or expansion
does not depend on the surface geometry but rather on how the whole
machine is configured and the rotor’s direction of rotation.
Both types of foils are very similar in their shape and can therefore be
obtained with analogous manufacturing processes. The foils have to be
joined together by their edges through a welding process, adhesive
application, slot fittings in rotors that can be dismantled or any other
convenient method. The possibility of using a fabrication process
allowing for the building of the rotor in a single element without the
need of manufacturing separate foils and their posterior joining, is not
Figure 4 exemplifies how the active and passive surfaces would be
consecutively and alternatively joined in order to build a rotor.
Figure 5 illustrates different perspectives of a complete rotor. Notice
how the passive surfaces nearly hide the active surfaces.
With the goal of demonstrating the arrangement of the dynamic symmetry
foils rotor intended for an axial flow, Figure 6 shows a perspective of
an axially cut basic gas turbine engine where arrows indicate its
rotation direction and the paths of its internal gasses.
Figure 7 shows a schematic section of the same engine. A clean air flow
14 enters the engine and reaches the rotor 15 passing through its
compression passages. The partially compressed air then exits the rotor
with great kinetic energy at 16. The air is then conducted through
a spiral volute to the combustor intake 17, where it is fully
compressed and loses most of its kinetic energy. It exits the combustor
18 after having thermal energy added to it and is conducted up to 19
through another spiral volute where part of its pressure has been lost
and great kinetic energy has been gained. It then enters the expansion
passages of the rotor 15 where it yields part of its energy to the rotor
and finally leaves the engine at 20.
Notice the rotor has been qualified as one of axial flow since this
configuration does not take advantage in any way of the radial component
of the flow, that is, the compressing flow circulates towards the
rotation axis and the expanding flow moves away from it.
In real applications these dynamic symmetry surfaces will unlikely
present any geometric symmetry due to the disparity in thermodynamic
conditions among the expanding and compressing flows. The real foil
surfaces with which the rotors will finally be built will be derived
from the theoretical criterion of dynamic symmetry whilst attending to
resistance requirements, mechanical fluids optimization, heat transfer
considerations and suitability of the specific application for which it
is being designed. It is not assumed that foils feature a uniform
thickness, which will depend on the design needs of each case.
The drawings and simplified schematics presented in this document are
offered as examples and do not correspond to actual designs. Since they
are highly didactic, the previously shown figures represent surfaces
designed for axial flows. The fact that the flow type be predominantly
radial or axial is something merely circumstantial and does not alter
the application of the dynamic symmetry criterion.
In order for an energy transfer between the rotor and the fluid to
exist, motion (rotation) and force (pressure) are needed. The pressure
differential existing between the surface and the fluid is caused by the
accelerations of the latter, that is, speed changes in the fluid both
in modulus and direction. The speed change in the fluid may be due to
the surface curvature, as in the axial flow, or to the speed change of
that very surface at different distances from the rotation axis, as in
the radial flow, or may be due to a mixture of both reasons. When
intended for axial flows, the dynamic symmetry surface has a double
curvature and its shape resembles a horse saddle. When intended for
radial flows, the dynamic symmetry surface could be flat since the speed
changes don’t depend on the existence of a curvature but on the greater
or lesser proximity to the rotation axis. From a geometrical point of
view, the dynamic symmetry surface intended for radial flows may be
considered as a limit to that of axial flows in which the
curvature is null.
Independently from the rotor configuration, flows in which the surface
curvature is responsible for the fluid accelerations that further
contribute to the energy transfer between the rotor and the fluid, are
known as axial; flows in which the variation of distance from the
rotation axis is the main cause for the fluid accelerations that further
contribute to the energy transfer between the rotor and the fluid, are
known as radial; flows in which both the surface curvature and the
variation of distance from the rotation axis are responsible for the
accelerations that further contribute to the energy transfer between the
rotor and the fluid, are known as mixed.
A schematic axial section of a turbo-prop engine with dynamic symmetry
foils rotor 15 intended for axial flows, whose combustion chamber 31 is
centred, is shown in Figure 8.
The rotor is akin to the one shown in figure 5.
The engine body is composed of an exterior casing 38 and a central body
40 connected by a stator 39. The propeller blades are part of an
external rotor 37 that has an internal stage of conventional blades 35
to assist the compression and another stage of conventional turbine
blades 36 which drive the whole external rotor with the exhaust gasses.
In this case, the rotor built with dynamic symmetry foils 15 is only
used for compression while the output power is obtained with the blades
36 of the exterior rotor 37. The exterior rotor 37 and the dynamic
symmetry foils rotor 15 are counter rotating.
Fuel and electrical ignition are supplied to the combustion chamber 31
through the conduct 33. The engine can be started with the injection of
compressed air from a bottle into the combustion chamber through conduct
33 and, once started, the same conduct 33 can be used to refill the
same bottle with compressed air taken from the combustion chamber inlet.
The flow of clean air 14 is partially accelerated and compressed by the
blades 35 of the exterior rotor 37 and reaches the rotor 15 passing
through its compression passages. It then exits the rotor 15 and enters
the compression spiral volute 30 which leads it to the combustion
chamber 31. After having thermal energy added to it, the flow exits the
combustion chamber and enters the expansion spiral volute 32 which
brings it up to the rotor 15. The gas passes through the expansion
passages of the rotor 15 where it yields part of its energy. After
leaving the rotor 15 it acts on the turbine blades 36 delivering its
power to the exterior rotor 37 before finally exiting the engine at 20.
Rotors intended for mixed flows are essentially equal to those intended
for axial flows albeit the machine configuration does allow benefiting
from the radial component of the flow in the compression or expansion
Figures 9 and 10 show two axially cut views of a turbo-fan engine driven
by a dynamic symmetry foils rotor intended for mixed flows, in which
the rotor’s sense of rotation is indicated.
Figure 11 shows the schematic of the previously described turbo-fan
engine’s axial section. The engine can be started injecting compressed
air from a bottle into the combustion chamber, which is external.
The fresh air entering 14, passes through the compression passages of
the rotor 15. The majority of the air is expelled at 48, obtaining
thrust, whilst the rest of the pumped air is directed to the compression
volute 30, and from there, up to the combustion chamber. After having
thermal energy added to it, the air exits the combustion chamber and
enters the expansion volute 32 which then conducts it up to the rotor
15. The gas passes through the expansion passages of the rotor 15 where
it yields its energy and is finally exhausted to the exterior at 20. The
air used for thrust 48, is forced to pass through a stator 49 before
escaping the engine.
Notice how the rotor has been described as a mixed flow one since this
configuration does take advantage of the radial component of the
compressing flow; that is, it moves away from the rotation axis
while the expanding one circulates towards it.
The next figures clearly show this rotor’s foil geometry which is
designed to pump a great volume of air through its central zone while
not giving it too much speed.
Figure 12 shows perspectives of the joint between one dynamic symmetry
passive surface and two dynamic symmetry active surfaces of the rotor 15
of figure 11. Notice the wideness of the compression passage with
respect to the expansion one. The left view gives a better appreciation
of the inlet zones from both the compression and expansion passages,
while the right view gives a better appreciation of the outlet
The radial flow can be considered a limit case of a mixed flow in which
the net curvature of the flow is null and, thus, a radial rotor designed
with the same techniques as a mixed one would be perfectly feasible.
However, the design flexibility provided by the dynamic symmetry
criterion allows for more advantageous radial flow solutions. As will be
demonstrated in the following figures, it is possible to manufacture a
dynamic symmetry foils rotor in which the compressing flow does not need
to forcibly overcross the expanding flow, and in which it is
unnecessary that the passages be completely shaped by the active and
Figure 13 shows a schematic diagram for the axial section of a
turbo-machine that uses a radial flow dynamic symmetry foils rotor 15 in
order to exchange energy between two fluid currents. The figure also
shows a perspective of a dynamic symmetry active surface 1 of that
rotor. The paths of the expanding flow 2 and compressing flow 3 can be
seen represented through of arrow strips.
Notice that in the central area, both the expanding flow 2 and the
compressing flow 3 circulate almost parallel without their paths ever
The fluid being compressed enters the turbo-machine at 14, near the axis
of rotation, continuing to the compression passages of the rotor 15
where it receives energy by radially circulating up to the volute 56 on
the periphery. The expanding fluid arrives through volute 57, on the
periphery, passes to the expansion passages of the rotor 15 where it
yields its energy by radially circulating towards the rotation axis and
finally leaves the turbo-machine at 20.
Figure 14 shows perspectives of the rotor 15 from figure 13. One of the
most differentiating characteristic of this radial flow dynamic symmetry
foils rotor with respect to those intended for axial or mixed flows is
that the compression and expansion passages are not sealed between the
active and passive surfaces but rather one part of them must be sealed
by the turbine housing, as can be seen at point 55 of figure 13. This is
also a common characteristic in conventional radial turbo-machines.
This area of the passages sealed by the housing coincides with the area
in which the expanding flow 2 and the compressing flow 3 circulate in an
almost parallel direction.
In this example the geometry of the surfaces is very simple: a flat
active surface and a passive surface close to a ruled surface. With this
design being perfectly feasible, it can still be optimized giving the
adequate warp to the surfaces in order to better fit the axial type flow
predominant in the areas close to the rotation axis such as is shown in
the following figure.
This same optimization to an axial type flow predominant in the areas
close to the rotation axis can also be achieved using fins, obtaining a
similar effect with less forced geometries, as shown on the rotor of the
following figure. These fins, as opposed to dynamic symmetry surfaces,
are bathed by the same fluid on both sides, that is, they are merely a
prolongation since once isolated and contrary to the rest of the
surface, they fail to comply with the dynamic symmetry criterion. They
could also easily be used in dynamic symmetry foils rotors intended for
axial or mixed flow, although they are especially convenient for radial
ones since a markedly axial flow area usually exists.
Dynamic symmetry foils rotors are also susceptible of being combined in
multi compression-expansion stage constructive solutions as those shown
in next figure.
Since rotors not only interact with the fluid but are also integrated in
a machine, it will usually be necessary for them to be adapted so as to
perform other functions. Thus, the foils can optionally present
appendixes on specific parts of their edges in an assembly wing fashion
which can serve as a bearing, airtight seal, balancer, foil assembly
point in demountable rotors or to house other accessories.
Figure 18 shows a perspective of a dynamic symmetry passive surface on
which some appendages named assembly wings have been added to the free
edges. These assembly wings are simply extensions of the surface
structure that can be used in several ways according to the convenience
of the application. They are present on the passive surface due to its
free edges, but they could just as well be on the active one. They
usually serve as bearings in order to transmit efforts to the
turbo-machine structure into which the rotor is integrated, also as a
surface on which to effect an airtight sealing, as a support for rotor
driven accessories, or as assembly point for other elements. When
integrating several rotors in the turbo-machine, it is probable that
both the sealing and effort transmission takes place between these very
rotors in addition to taking place between the rotor and the
turbo-machine. Furthermore, the assembly wings will host the
counterweights derived from the balancing operation of the rotor.
The following figure shows a perspective of a sectioned electric
generator, useful in illustrating various aspects. The dynamic symmetry
foils rotor intended for axial flows is equipped with assembly wings 22
which act as a bearing and airtight seal along with a support for an
outer 23 and inner 21 ring.
Whilst, from an operative point of view, these rings are not essential,
they become convenient due to the fact they are elements with a
continuous structure and can therefore conform to more detailed designs
requiring a single milling process. These rings could obviously be
joined to the foils without requiring assembly wings. These rings can be
used to perform the same functions as the assembly wings and, in
particular, act as a chassis for the tuning of dynamic symmetry surfaces
in demountable rotors. A reasonable technique in the building of
demountable rotors intended for axial or mixed flows would be to use the
set resulting from welding an active surface, with no assembly wings,
and a passive surface, which does have assembly wings on its free edges,
as a constructive element.
Additionally, the outer ring 23 contains the mobile electromagnetic
elements 9 as accessories which interact with the fixed elements 10,
embedded into the machine structure.
After hiding from view the rotor and its rings, a detailed view of the
combustion chamber of that generator located in its central zone, is
shown next. The air flow being compressed 3 enters the compression
spiral volute after exiting the rotor compression passages and reaches,
compressed, the combustion chamber where it receives thermal energy.
Next, the hot gasses flow 2 is conducted from the combustion chamber
towards the rotor expansion passages through the expansion spiral
It is to be expected that these kind of designs present several
advantages such as eliminating the need of a shaft to transmit the power
from turbine to compressor, diminishing the length and weight of the
engine, rotors materials are better refrigerated allowing for greater
operational temperatures and a lower diluted air ratio, the
refrigeration process itself involves a heat recovery effect improving
overall thermal efficiency, the foils suffer less mechanical stresses
thanks to partial compensation of the fluid pressure on both sides of
its surfaces. The obligation to cross the compressing and expanding
fluids in the same rotor does not necessarily imply having to provide
notably larger sections than that of conventional rotors, since what is
sought and achieved with the dynamic symmetry is to exploit otherwise
unused spaces of conventional rotor blades, particularly if the use of
high pressure geometries is intended. It is also significant that the
lower inertia of the rotors allows for the injection of compressed air
directly into the combustion chambers as a starting procedure thus
allowing for the replacement of otherwise heavier and slower
When embracing the dynamic symmetry criterion, 2D classic design
methodology is left aside in favour of more powerful modern engineering
tools in order to concentrate the technological effort in the
unconventional 3D geometries design of two warped foils and their later
manufacture. Although this technology is at a very early development
phase, it is necessary to mention that, apart from its operative
advantages, a lot of trust has been put in the building technique of the
rotors where joining two types of warped foils could constitute an
important new step in the industrial process of gas turbine
Whilst these claimed advantages are desirable in any gas turbine engine
application, the dynamic symmetry concept may be particularly useful in
low power turbines and micro-turbines, portable power generation units,
distributed electrical power generation, auxiliary engines for vertical
lift on VTOL aircrafts, primary generators in hybrid propulsion, quick
start turbine engines, turbo-blowers, etc.
One promising application of this technology is found in military
applications where the automated manufacturing of disposable dynamic
symmetry foils rotors could lead to a new generation of very economic
power plants intended for motorizing unmanned combat machines or cruise
missiles. These kinds of platforms, designed for a single use or a
limited operative life expectancy where maximum simplicity without
renouncing to efficiency is pursued, would allow the reduction of costs
of not only the production but also the preventive maintenance, reducing
these operations only to the full replacement of rotors.
the prior state of the art
It is well known that one of the most limiting factors in gas turbine
design is the high combustion temperature needed to achieve good
efficiency, although this adversely affects the materials resistance. In
order to solve this problem, apart from improving alloys, several
techniques whose purpose is to cool the blades from the hot gases have
been proposed, allowing them to work at higher temperatures. Systems
based on incorporating the blades with cooling circuits through
more or less complex channels in which a refrigerant fluid must
circulate already exist. Another system uses porous materials or
mechanizes orifices at strategic intervals in order to keep the blade
surface covered with a thin film of cold gas injected under pressure
from its core, isolating the blades from the high temperatures of
exhaust gases. There is yet another system which exploits the idea of
using the hollow
blades of a conventional axial turbine as a radial compressor forcing
the fresh air to circulate through its interior before entering the
combustor to later redirect the hot gases proceeding from the combustor
through a loop against the blades of the axial turbine. In this way, it
is possible to cool the turbine blades which act simultaneously as a
radial pump and axial motor.
This hollow blade based system, although not exactly considered an
antecedent, does show an important parallelism with the dynamic symmetry
criterion due to the fact that the fresh compressed air is also in
charge of directly refrigerating the rotor surfaces in contact with hot
gases proceeding from the combustor, having it act as a pump and a motor
at the same time. Nonetheless, the idea of conceiving a hollow blade as a conduct through
which the air can circulate radially, although useful and very
intuitive, imposes certain limitations that can end up being potentially
inconvenient since it conditions the machine configuration where it
forces the exit location of the compressed air flow towards the
periphery of the rotor and, at the same time, the tubular geometry of
the blades conditions the radial flow transitions to and from the rotor.
These limitations can be solved thanks to the dynamic symmetry strategy
which provides smooth inflow and outflow profiles without the need to
add strange elements intended to eliminate discontinuities in the flow
and, at the same time, allows for innovative constructive solutions with
respect to hollow blades avoiding the constraints of radial compression
and conventional shapes of existing blades.
Warning for bias of rejection to the unknown
Fear and scepticism are natural reactions to new ideas or radical
changes and can result in a misleading perception of a reality that is
usually much simpler than it first seems. All gas turbine engines have a
compressor, a hot gases turbine and, if circumstances permit, a cooling
and a heat recovery system to increase its efficiency. Dynamic symmetry turbines have the exact same elements, but thanks to
its innovative architecture, all those elements are integrated simply in
a lightweight and compact rotor. Based on this, dynamic symmetry has
never been conceived as a hypothetical technology, it is to say, it is not being researched to find out if it can work, but to find out the best way to make it work.
Nonetheless, during the dissemination phase of this technology, it has
been established that some people suffer from an immediate and unfounded
"rejection effect" when seeing the geometry of a dynamic symmetry foils
rotor for the first time. The operation of the rotors and curvature of
the surfaces, distant from conventional ones, can sometimes cause first
impressions to consider it something extraordinarily complex and that it
would probably present flow quality problems and make it hardly viable.
It is true that the passages through which the fluid circulates in a
dynamic symmetry foils rotor are enclosed by surfaces with a striking
warping that confer to the same capricious shapes.
Different perspectives of one of these passages, bounded by surfaces
with strange warping and tortuous shapes, are illustrated in the
previous figures. At first sight, it could be intuited that such a
geometry is unsuitable in obtaining a flow under optimal turbine working
The rotor depicted in the previous figures, corresponds to an absolutely
conventional centrifugal compressor, and not a particularly modern one
either, similar to those used in many small power gas turbines or in
supercharging systems of explosion engines. Since it is conventional, seeing it does not cause the impression that
flow quality problems should appear when fluid circulates through its
passages. Figures 38, 39 and 40 do not correspond to the passage of a
dynamic symmetry foils rotor but to the conventional centrifugal rotor
previously shown. Despite the conventionality of its architecture, any
expert knows that if it is poorly designed or simply operated outside
its design parameters, it will also perform poorly.
Dynamic symmetry is a very innovative design concept from an
architectural point of view, but from a fluid dynamics point of view,
dynamic symmetry turbines are not so different from conventional ones.
All of them comprise compression and expansion passages delimited by
streamlined surfaces with the necessary curvatures and orientations to
perform their respective functions. Passages are simply conduits through which a fluid circulates and these
can be designed in many different ways. Some of them will apparently
seem more conventional and other less, but the behaviour of the fluid is
not conditioned by the mere fact that the geometry appears conventional
or not. As a result, there is no objective reason to predict problems
in dynamic symmetry that may not equally occur in any other conventional
design and that cannot be treated in exactly the same way.
Its physical viability has never been in question, but, as with any
other novelty, uncertainties exist and a prudent approach requires
conducting systematic research leading to quantitative results.
Simply put, detailed studies are planned that allow for the discovery of
the best design practices when implementing the philosophy of dynamic
symmetry in order to be able to leverage its advantages and come to
grasp its limitations and peculiarities.
To associate a high degree of innovation with a high probability of
malfunction without any explanation is, blatantly, an absurd behavioural
predisposition. In the end, the good or bad functioning of a design
will depend on the quality of the engineering work that has been
invested in it, such holds for conventional turbine as well as
non-conventional ones. For this reason, any expert studying the dynamic symmetry criterion
for the first time, must be warned from the possibility of suffering
this relatively common cognitive prejudice that triggers
spurious conclusions not based on careful scientific analysis but on a
subjective and hasty first impression of something that breaks out the
Although the dynamic symmetry criterion is intended to simplify and
improve the construction of gas turbines, it must be kept in mind that
the characteristics of dynamic symmetry foils can almost never be
assimilated to a two-dimensional geometry, thus, its understanding
requires a sufficiently developed spatial vision and a set of 3D
Basic design considerations for a micro-turbine
One of the major current challenges in the gas turbine industry is the
production of very small power turbines capable of offering similar
efficiencies to that of large ones. The simplest micro-turbine has one
compression stage and one expansion stage coupled on the same axis. A
qualitative analysis of some features that would influence the design of
a micro-turbine equipped with a single dynamic symmetry foils rotor is
carried out with this premise.
The simplest configuration for the intended purpose is that
corresponding to a mixed flow rotor, i.e., one compression-expansion
stage as represented in the longitudinal section of Figure 22. A dynamic
symmetry foils rotor intended for radial flows could also be used
although it has been estimated that the mixed flow one has the advantage
of only being in contact with the casing through the assembly wings
ultimately requiring less precision in its manufacture.
Logically, the accessible part of the shaft resides in the air intake
area protected from heat and the aggressive elements of exhaust gases.
In addition, this allows for a better balancing of the rotor geometry
where the pass-through section required for the intake nozzle, and for
thermodynamic reasons, is smaller than that of the exhaust.
It should be remembered that both the pressure and suction surfaces
simultaneously delimit the expansion and compression passages and,
therefore, the geometry of any of them affects both types of passages.
However, it is true that the compression passages are affected mainly by
the curvature in a particular direction, whilst expansion passages are
affected mainly by the curvature in the other direction, as shown in
The most energetic fluid flow is the one exiting the combustion chamber,
reason by which the considerations carried out with respect to the main
curvatures of the expansion passages will condition the rotation speed,
speed to which the main curvatures of compression passages will
subsequently have to be adapted.
The amplitude of the inlet section of the expansion passages will grow
as the component parallel to the axis plane of the absolute velocity
vector with which the gases leaving the combustor affects the expansion
passages gets smaller. Although dynamic symmetry allows for a flexible
design, in order to achieve less forced geometries, especially for the
suction surface, it becomes convenient to provide a fairly wide entry
section for the expansion passages. This is accomplished by making the
angle of incidence of the gases from the combustor tangent enough to the
turbine. This will also contribute to reduce the aerodynamic axial
thrust corresponding to the expansion passages.
Once chosen the rotation speed depending on the expansion passages
needs, the compression passages outlet usually results significantly
narrow in comparison with the inlet. This is normally not a problem for
the design since on the other side of that active surface area, the
expansion passage is very thin and leads a small proportion of the
To achieve a not too high rotation speed in a turbine with a single
expansion stage, which has to absorb all the power, working with high
pressure geometries is needed, implying that the pass through area of
the passages narrows towards its central part with respect to the inlet
or outlet (fig. 50). This is achieved naturally by employing the dynamic symmetry strategy.
Nonetheless, the design offers many degrees of freedom and it can be
resorted to the centre widening technique in order to accommodate better
the pass through section, as shown in Fig. 48 and 49.
In reality, to obtain a low rotation speed, this is not the only factor
to consider for the geometry. In a dynamic symmetry turbine, cooling and
heat recovery should be clearly differentiated. Both objectives are
achieved through the same physical mechanism, that is, the heat transfer
between the compression and expansion passages, although they involve
different conditions. If the only interest is cooling, it would be
desirable to use some coating material over the surface of the expansion
passages which, beside from chemical protection, provides thermal
insulation. In the case of heat recovery the impact of such coating
would have to be evaluated along with the amount of exchange surface
related to the number of pairs of rotor foils. In addition, heat recovery is effective when residual heat is recovered,
i.e., after extraction of the useful power from hot gases, implying
that these gases circulate in certain conditions finally having a great
influence on the foils geometry.
The use of high pressure geometries would also involve, in general, the
use of sharp leading edges. Although it is a decision that depends on
fluid dynamics criteria, sharp edges can be particularly interesting if
the expected construction of the rotor is to be carried out by welding
of the foils.
Unlike conventional designs, here the passage section is not
approximately trapezoidal but shaped as a sheath tuned at the ends. This
can affect the fluid speed at the inlet and outlet of the passages
presenting a distribution where it would be lower near the ends and
higher at the centre.
To find out up to what extent this phenomenon manifests itself, a simple
fluid mechanics calculation with the preliminary geometry of the rotor
can be carried out, obtaining a qualitative understanding of such
distribution thus enhancing the initial dimension calculations of inlet
and outlet sections of the rotor passages.
In addition, useful qualitative knowledge about the most appropriate
distances between pressure and suction surfaces can also be obtained
through this calculation in order to avoid flow separation or excessive
The area joining the foils to the shaft must be capable of transmitting the aerodynamic torque to the latter.
A pressure surface is joined to the next suction surface by the blue
stripped edges, shown in Figure 52, to form the compression passage. In
turn, this suction surface is joined to the following pressure surface
by red stripped edges to form the expansion passage, and so on.
In the area uniting them to the shaft (fig. 53), the interference
between foils creates a bulk of material used for the union. Although
the geometry of the joining region can easily be modelled in a
streamlined way, this zone is not particularly important from a fluid
dynamics point of view, and then it can easily be adapted to fulfil its
role. Sizing the shaft is simple and the rule that the area of the
cylindrical surface in which foils join the shaft must be equal to or
greater than the area of the section of the same shaft can be set as a
preliminary design standard.
micro-turbine: rotor geometry
As a first application exercise of the dynamic symmetry strategy, a 100
kW shaft output power micro gas turbine configured with a single mixed
flow rotor is projected. This study will allow for an insight into more
realistic geometries and for a comparison of the obtained results with
other conventional micro turbines. The following conditions will be
considered in the design:
The design optimization process will seek for maximum efficiency and
minimum rotor weight that allows for the previously mentioned
requirements. Hereafter, the steps leading to the preliminary model
later evaluated and optimized through numerical calculation software,
- The shaft output power will be 100 kW ± 5 kW.
- The rotor will be made of INCONEL 738 or a similar material intended for turbines.
- The fuel will be gasoline or a similar liquid fuel.
- Standard Air: 15 °C, 760 mm Hg.
- The usual industry safety margins will be used.
The first step in order to work with the dynamic symmetry philosophy is
to free oneself from prejudices and constrains blocking originality and
to clarify some concepts that are important to keep in mind throughout
Taking into account the previous constraints, assuming tentative values
for certain parameters and using the elemental thermodynamic formulae of
the Brayton cycle, it is possible to estimate the operating variables
of the turbo-machine and inlets and outlets areas of the compression and
expansion rotor passages. With those data an axial cutaway of the
micro-turbine can be sketched. Using velocity triangles the main fluid
orientations at the inlets and outlets of the passages are calculated
which, in turn, allows for the drawing of the basic three-dimensional
curves which will define the rotor foils geometry.
- To innovate is essentially to step out of line, but if
something is unconventional, it does not necessarily mean it is absurd
or very complex.
- Flow paths don’t need to be two-dimensional or near
two-dimensional. A fluid can have a three-dimensional path since what is
really important are the thermodynamic conditions at the beginning and
end of these paths.
- Surfaces on which the flow passes need not to be
approximately developable nor do they need to correspond to extruded
two-dimensional profiles. A three-dimensional geometry with irregular
warping can also correctly conduct the fluid if properly designed.
- Often, a characteristic that produces negative effects
simultaneously provokes positive ones which must be weighed before
- A dynamic symmetry foils rotor is simultaneously a
compressor, turbine and heat recovery. This interaction causes its
design to have more degrees of freedom than that existing in each
element separately, but only one element is designed, not three.
Then, working in the 3D modeller, a smoothed dynamic symmetry pressure
surface is designed with its edges oriented according to the flow’s
velocity vectors relative to the surface.
As was foreseeable, the very different thermodynamic properties of the
compressing and expanding flows cause the actual geometry to be quite
different from the theoretical symmetry. Note how the compression
passages have their outlets oriented perpendicular to the rotation axis
in order to avoid the axial component of the thrust generated by the
compressed air flow whilst the same thrust counteracts the centrifugal
force on the foils. Reducing the pressure at the outlet of the
compression passages forces the flow speed to increase. This may not
make much sense in a conventional design, but in a dynamic symmetry
foils rotor, the resulting temperature reduction could improve
refrigeration, converting it into a factor to consider. After
tentatively choosing the number of pressure surfaces, the appearance of
the rotor can be visualized with the absence of suction surfaces. It is
to be considered that a large number of foils worsens the
manufacturability and increases the contact surface with its associated
performance losses, but, in turn lessens the load on them and enhances
the heat recovery effect.
To design the dynamic symmetry suction surface, the defining curves of
the pressure surface are conveniently deformed so as to model the
compression and expansion passages to the appropriate size for the
thermodynamic conditions encountered in their respective fluid streams.
Notice that in the dynamic symmetry foils rotor, the passages are
tighter at the area joining the pressure and suction surfaces, thereby
making the design of the central zone geometry more important than the
design of the edges conducting a minor flow proportion.
Finally the complete preliminary design of the micro-turbine rotor is
obtained. After assigning a provisional thickness to the foils and
meshing the model, it can be introduced in the numerical calculations
program and until the optimum result is reached, several configurations
of injected fuel quantities, rotation speeds, thicknesses, number and
geometry of the foils will be tested. Although this preliminary design
is based on technically consistent calculations, there are many degrees
of freedom and it is to be expected that the optimization process leads
to a substantially different and evolved design. Furthermore, phenomena
to be prevented such as flow separation, instability or vibrations may
also decisively influence the final design.
100 kW micro-turbine: final configuration
Illustrative view of a defoliated rotor resulting from optimization:
Once the foils geometry has been optimized, details for its final
configuration have to be chosen. The assembly wings on the free edges of
the passive surface 22 will serve both as a support to transmit the
efforts to the housing and as an airtight seal.
The chosen arrangement allows for an easy axial assembly of the whole
turbomachine. Assuming that, for the prototype, an external can
combustor instead of an annular combustion chamber will be used, only
three parts are needed for the casing: an air intake nozzle; a block
integrating the diffuser, inductor, compression and expansion
collectors; a discharge nozzle. Normally, the rotor assembly wings will
lay on bearings specifically designed for this purpose.
Should the rotor be manufactured by welding the foils, the suggested
procedure consist of a first phase in which they are welded in pairs, a
pressure and a suction foil. In the next phase, all the pairs of the
rotor are placed in a positioning rack to weld them together. In the
last stage, the shaft is welded to the set of foils resulting from the
previous phase. There will usually be an additional phase in which the
assembly wings are rectified to ensure their geometry is within
tolerance and the welded joints are brushed up.
Finally, a compact rotor is obtained, lightweight, self-cooled and with an
integrated heat exchanger. Hereafter are several views of the rotor with
shaft and assembly wings (all elements are illustrated in the same
Assembled turbomachine ready to be connected to the combustor:
The turbomachine configuration allows for an easy axial assembly. The
following figure shows an exploded view which, in order of assembly from
left to right, includes: an air intake nozzle, a block of volutes, a
transverse thrust bearing, an axial thrust bearing, a rotor, another
axial thrust bearing and the discharge nozzle.
The following figures show a cutaway of the turbomachine:
All the exercises performed in the previous investigations will
constitute a valuable guide of good practices and learnt lessons for the
final design of a technological demonstrator that can be proven on a test bed. Previously to this step, some transcendent
decisions must be made such as the rotor manufacturing process, the
selection of the appropriate alloy suited to the process with which the
rotor will be manufactured, or whether to apply a coating material,
especially in a case where it affects the thermal conductivity of the
This article has been redacted as an instrument to disclose the
technology of dynamic symmetry turbines from the specification part of
the international patent application PCT/ES2012/000078.
Original patent application as filed PCTES2012000078
Patent application translated into english PCTES2012000078_EN
Original patent application as published WO2012098277
International search report ISR
Permalink to the WIPO site http://patentscope.wipo.int/search/en/WO2012098277
This document can be reproduced citing the source. Images are linked to their respective high resolution originals.
In the case of being interested in exploiting this technology a primary
contact can be established through an e-mail notification to the address
indicated in the contact paragraph included hereafter.
Comments, suggestions and criticism about this innovation are welcome.
They should be directed to the attention of Juan Andrés Hurtado.