FR3112369A1 - Turbomachine counter-rotating compressor - Google Patents

Abstract

A turbomachine counter-rotating compressor (10) comprising:a rotor (16); a plurality of first blade stages (1) mounted on the rotor (16) so as to drive the first blades (1) in a first direction of rotation of the rotor (11);at least one second blade stage (2) mounted between the first vane stages (1); said compressor (10) further comprising,at least one electric motor (21);at least one stage of second blades being driven in rotation by said at least one first electric motor (21) in a second direction of rotation contrary to the first direction rotation. Figure for abstract: Fig. 4

Description

Turbomachine Counter-Rotating Compressor »

GENERAL TECHNICAL AREA

The invention relates to turbomachine compressors and more particularly counter-rotating turbomachine compressors.

STATE OF THE ART

A turbomachine conventionally comprises, from upstream to downstream in the direction of gas flow, a fan, several compressor bodies (low pressure, high pressure and possibly intermediate), a combustion chamber and several turbines.

FIG. 1 illustrates a two-spool turbomachine comprising, upstream to downstream, in the direction of gas flow (along the engine axis AA), a fan 20, a low-pressure compressor 11, a high-pressure compressor 12, a combustion chamber 13, a high pressure turbine 14 and a low pressure turbine 15.

The low pressure compressor 11 is driven in rotation by the low pressure turbine via a low pressure shaft 16 and the high pressure compressor is driven in rotation by the high pressure turbine via a high pressure shaft 17 .

A compressor generally comprises an annular casing inside which a succession of rotor and stator stages are arranged. Each stage comprises one or more blades. The blades of the rotor stage are driven in rotation by a transmission shaft mechanically driven by a turbine while the blades of the stator stage are fixed on a stator.

The advantage of having several compressor bodies is to optimize the thermopropulsive efficiency (and more specifically its thermal component). However, this architecture imposes design compromises detrimental to the efficiency of each stage.

An alternative to this compressor architecture is a compressor composed exclusively of counter-rotating rotor stages. From then on, the stages of stator blades are replaced by stages of rotor blades rotating in the opposite direction to the initial rotor blades.

A counter-rotating compressor architecture is illustrated in FIG. 2 and notably comprises a first rotating shaft A1 and a second rotating shaft A2, each shaft being driven in rotation by two independent and counter-rotating turbines 161, 162. Each shaft A1, A2 drives in rotation the blade stages 171, 172 of the upstream compressor. Thus, it will be understood that to pass from the configuration of FIG. 1 to the configuration of FIG. 2, the stator vanes of FIG. 1 are now mobile in rotation. To do this, an external or internal casing to which the blades are linked is linked to the turbines. It is therefore the rotation of the casing which causes the corresponding blades to rotate.

The use of a counter-rotating compressor is advantageous because it makes it possible to obtain a higher compression ratio per compression stage than that of a conventional compressor. In addition, for the same compression ratio, it makes it possible to reduce the number of compressor stages.

Although advantageous, a counter-rotating architecture is complex since several rotating shafts are required.

In addition, turbomachine compressors may be subject to the surge phenomenon. Pumping can cause serious damage to the compressor. In order to limit the risks of surge, it is customary to equip compressors with a mechanism for variable wedging of the blades of the stator stages and to add relief valves. These mechanisms further complicate the architecture of counter-rotating compressors.

PRESENTATION OF THE INVENTION

The invention makes it possible to overcome the aforementioned drawbacks by simplifying in particular the architecture of a counter-rotating compressor.

To achieve this object, the invention relates, according to a first aspect, to a counter-rotating turbomachine compressor comprising: a rotor; a plurality of stages of first blades mounted on the rotor so as to drive the first blades in a first direction of rotation of the rotor; at least one second blade stage mounted between the first blade stages; said compressor further comprising at least one electric motor; at least one stage of second blades being driven in rotation by said at least one first electric motor in a second direction of rotation contrary to the first direction of rotation.

The invention according to the first aspect is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination:

- the rotor is driven in rotation by means of a second electric motor separate from each of said at least one first electric motor;

- the second blades of at least one stage of second blades are linked at their outer end by a ring, this ring being driven in rotation by one of the at least one electric motor;

- each first electric motor operates independently of the other first electric motors;

- At least one of the at least one first electric motor is asynchronous.

The invention relates, according to a second aspect, to a turbomachine comprising a turbine, a drive shaft and a compressor according to the first aspect of the invention, the rotor being driven in rotation by the turbine.

The invention according to the second aspect is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination:

- a first and/or an electric motor is powered by the turbine via an electricity generator;

- the turbine comprises counter-rotating stages, each stage of the turbine being configured to rotate one stage of a compressor.

- It comprises a casing in which is housed a compressor according to the first aspect of the invention, in which at least one of the electric motors is arranged on the casing.

The invention relates, according to a third aspect, to an aircraft comprising a turbomachine according to the second aspect of the invention.

The invention makes it possible in particular to avoid the use of two rotating shafts and therefore to simplify the architecture of the compressor.

PRESENTATION OF FIGURES

Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and not limiting, and which must be read in conjunction with the appended drawings in which, in addition to Figures 1 and 2 already discussed:

FIG. 3 schematically illustrates a turbomachine comprising a counter-rotating compressor according to the invention;

FIG. 4 schematically illustrates a turbomachine comprising a counter-rotating compressor according to one embodiment of the invention;

FIG. 5 schematically illustrates a turbomachine comprising a counter-rotating compressor according to one embodiment of the invention;

FIG. 6 schematically illustrates a turbomachine comprising a counter-rotating compressor according to one embodiment of the invention;

[Fig. 7]

Figure 7 illustrates a compressor according to one embodiment of the invention.

In all the figures, similar elements bear identical references.

DETAILED DESCRIPTION OF THE INVENTION

FIG. 3 schematically illustrates part of a turbomachine on which is visible a compressor 10, a combustion chamber 13 and a turbine 14, an annular flow space delimited by an outer casing 24 and an inner hub 25 having an axis of AA rotation. In what follows, the terms "inner" and "outer" are defined with respect to the motor axis AA.

Compressor 10 can be a high pressure, low pressure compressor and turbine 14 can be high pressure or low pressure.

The compressor 10 comprises stages of first blades 1 mounted on a rotor 16 rotating around an axis AA which is the motor axis according to a first direction of rotation.

The turbine 14 for its part comprises several stages of counter-rotating blades making it possible to drive one or more rotors of the compressor.

A succession of stages of second blades 2 is rotatably mounted around the rotor 16. In particular, stages of second blades 2 are mounted between the stages of first blades 1. There is then an alternation of first blades 1 and second blades 2 .

The first and second stages of blades 1, 2 are arranged in the annular space delimited by the outer casing 24 and the inner hub 25.

According to a first embodiment, illustrated in FIG. 4 , the rotor 16 is driven in rotation by a turbine 14 and constitutes a transmission shaft. The rotor 16 and the stages of first blades 1 are then driven in rotation in the first direction of rotation directly by the turbine 14.

Furthermore, according to this first embodiment at least one stage of second blades 2 is driven in rotation by at least one first electric motor 21 according to a second direction of rotation opposite to the first direction of rotation but around the rotor 16. FIG. 4 illustrates a configuration in which a stage of second blades 2 is rotated by means of a first electric motor 21 while another stage of second blades 2 is stationary. Figure 6 illustrates when it all the stages of second blades 2 are rotated by means of a first electric motor 21.

The stages of second blades 2 provide additional work to the work provided by the stages of first blades 1, thus making it possible to increase the compression ratio of the flow. The increase in the compression ratio thus makes it possible to reduce the total number of stages and therefore to reduce the length of the compressor 10. In addition, the stages of second blades 2 straighten the flow. This therefore makes it possible to avoid the use of stator vanes and thus to limit the size of the motor.

The second blades 2 can extend radially inwards, that is to say that the tip of the blade is closer to the motor axis AA than the root of the blade. Such an arrangement of the blades makes it possible to reduce the size of the engine.

Advantageously, each electric motor 21 drives in rotation the mass of a single stage of second blades 2. The mass driven in rotation by each first electric motor 21 being limited to a single stage of second blades 2, and not to a rotor on which all the stages of blades are mounted, this makes it possible to reduce the response time of the engine when changing the speed of rotation of the stages of second blades 2.

According to a second embodiment, illustrated in FIG. 6 , the rotor 16 can be rotated in the first direction of rotation by a second electric motor 23. This embodiment makes it possible to make the speed of rotation of the rotor 11 independent of the turbine 14 and therefore to control the speed of rotation of the rotor 16. The second electric motor 23 is independent of the first electric motor 21.

In a complementary way, as illustrated in FIG. 7 , each stage of second blades 2 is connected circumferentially to a ring 22. In this case, each second blade 2 of the same stage is connected to ring 22 by one of its ends. , for example by the foot of dawn. Ring 22 can, for example, be a ferromagnetic ring. Thus, each ring of each stage of second blades 2 is driven in rotation in the second direction of rotation by a first electric motor 21.

Advantageously, the first electric motors 21 can be asynchronous. In this case, each stage of second blades 2 can have a different speed of rotation. This embodiment also makes it possible to control and modulate the speeds of rotation of the stages of second blades 2, which makes it possible to preserve the pumping margins and thus the risks of pumping. Indeed, the control and the rapid adaptation of the speed of rotation of each stage of second blades 2 makes it possible to control the angle of attack of the second blades 2. Limiting the angle of attack of the rotor blades, in particular of the blades rotors of the compressor 10 furthest upstream, makes it possible to prevent the angles of attack from reaching a critical value causing the separation of the flow with the upper surface of the rotor blades. This therefore makes it possible to reduce the areas of detachment and to increase the detachment margins. The surge margins are thus increased because the surge phenomenon is generally preceded by the stall phenomenon. Consequently, a complex mechanism for variable pitch of the second blades 2, which conventionally makes it possible to control the angle of attack of the second blades 2, is no longer necessary. This makes it possible to simplify the architecture of the compressor 10. In addition, this makes it possible to dispense with the need for relief valves which make it possible, if necessary, to evacuate part of the overpressure in order to limit the risks of occurrence of the surge phenomenon. . This therefore makes it possible to further simplify the architecture of the compressor 10.

Additionally, the motors can be independent. The independence of the first electric motors 21 makes it possible to optimize the speed of rotation of the stages of second blades 2 so as to adapt the speed of rotation of each stage of second blades 2 to the different engine operating points. Thus, this makes it possible to reduce the energy consumption of the compressor 10, compared to a conventional counter-rotating compressor, by optimizing the speed of rotation of each stage of second blades 2.

In one embodiment, the first electric motors 21 driving the stages of second blades 2 in rotation can be arranged on the internal annular wall of the casing 24. The first electric motors 21 are then arranged opposite the stages of first blades 1.

In a complementary way, the turbine 14 can be connected to an electric generator 30. The electric generator 30 thus makes it possible to transform the mechanical energy supplied by the turbine 14 into electrical energy. The electrical energy produced then makes it possible to supply at least one of the first and second electric motors 21, 23 (see also FIG. 4). It will therefore be understood that each first electric motor 21 and/or the second electric motor 23 can be powered by energy coming from the turbine 14.

Alternatively, the first electric motors 21, 23 can, for example, be powered electrically by a combustion cell and/or an electric battery.

Alternatively, the electrical energy to supply the first and second electric motors 21, 23 can be taken from a particular location of the turbomachine, for example in electronic equipment of the turbomachine.

In one embodiment, a twin spool turbomachine may include a high pressure compressor, a low pressure compressor, a high pressure turbine, and a low pressure turbine. In this case, one or both compressors 10 can be as described above.

In addition, the turbomachine may also comprise a third so-called intermediate body, comprising an intermediate compressor and an intermediate turbine. In this case, some or all of the compressors 10 may be as described above.

Also, in addition, an additional turbine can be provided, in addition to that driving the rotor 16 or the electric motors in rotation. This additional turbine makes it possible, for example, to rotate the fan independently of the rest.

Thanks to the invention, it is possible to benefit from all the advantages of a counter-rotating compressor while limiting the complexity of its architecture.

Claims (10)

Counter-rotating turbomachine compressor (10) comprising:
a rotor (16);
a plurality of stages of first blades (1) mounted on the rotor (16) so as to drive the first blades (1) in a first direction of rotation of the rotor (11);
at least one second vane stage (2) mounted between the first vane stages (1);
said compressor (10) further comprising,
at least one electric motor (21);
at least one stage of second blades being driven in rotation by said at least one first electric motor (21) in a second direction of rotation contrary to the first direction of rotation. Compressor (10) according to Claim 1, in which the rotor (16) is driven in rotation by means of a second electric motor (23) separate from each of the said at least one first electric motor (21). Compressor (10) according to one of Claims 1 to 2, in which the second blades of at least one stage of second blades are connected at their outer end by a ring (22), this ring (22) being driven in rotation by one of the at least one electric motor (21). Compressor (10) according to one of Claims 1 to 3, characterized in that each first electric motor (21) operates independently of the other first electric motors (21). Compressor (10) according to one of Claims 1 to 4, characterized in that at least one of the at least one first electric motor (21) is asynchronous. Turbomachine comprising a turbine (14), a drive shaft (12) and a compressor (10) according to one of claims 1 to 5, the rotor (11) being driven in rotation by the turbine (14). Turbomachine according to claim 6, in which a first and/or an electric motor is powered by the turbine (14) via an electricity generator (30). Turbomachine according to one of Claims 6 to 7, in which the turbine (14) comprises counter-rotating stages, each stage of the turbine being configured to drive in rotation a stage of a compressor. Turbomachine according to one of Claims 6 to 8, comprising a casing (24) in which is housed a compressor (10) according to Claims 1 to 5, in which at least one of the electric motors (21) is arranged on the casing ( 24). Aircraft comprising a turbomachine according to one of claims 6 to 9.