CN118564343A

CN118564343A - Hybrid auxiliary power system capable of flexibly controlling air entraining flow

Info

Publication number: CN118564343A
Application number: CN202410607877.0A
Authority: CN
Inventors: 肖璆; 方波; 刘武; 林亲学; 尹军
Original assignee: Hunan Aviation Powerplant Research Institute AECC
Current assignee: Hunan Aviation Powerplant Research Institute AECC
Priority date: 2024-05-15
Filing date: 2024-05-15
Publication date: 2024-08-30

Abstract

The invention provides a hybrid auxiliary power system capable of flexibly controlling bleed air flow, which comprises a gas turbine engine, a compressor and a turbine, wherein the gas turbine engine is communicated with a pipeline for outputting bleed air, the compressor is communicated with the pipeline for outputting bleed air, and the compressor is configured to convey compressed air into the pipeline to increase the bleed air flow; a turbine is in communication with the gas turbine engine via a duct to exhaust a portion of the air from the gas turbine engine. The hybrid auxiliary power system with the structure and the flexible control of the bleed air flow can be realized by using the same gas turbine starter for different auxiliary power system bleed air requirements of an airplane by introducing a compressor and a turbine, and only the working state of the compressor or the turbine needs to be changed. Since the compressor, turbine and gas turbine engine are decoupled, the operating state of the compressor can be conveniently changed without changing the operating state of the gas turbine engine.

Description

Hybrid auxiliary power system capable of flexibly controlling air entraining flow

Technical Field

The invention relates to the technical field of aircraft engines, in particular to a hybrid auxiliary power system capable of flexibly controlling bleed air flow.

Background

Existing gas turbine auxiliary power units are commonly provided with the function of providing high pressure gas and output shaft power (electric power) according to aircraft requirements. Auxiliary power units are typically required to fulfil the following functions: providing a main engine starting energy source (high-pressure gas or electric energy), providing an aircraft environmental control system energy source (usually high-pressure gas, a few aircraft use electric energy), providing an aircraft ground maintenance and inspection energy source (usually electric energy), and providing electric and electronic equipment and electric energy for driving hydraulic equipment when the aircraft ground is stopped; providing an energy source (high pressure gas and electric energy) for emergency use in aircraft flight. The auxiliary power device enables the aircraft to start the main engine without depending on a ground power supply vehicle or an air source vehicle, provides environment-controlled air entraining and power supply under the condition of not starting the main engine, and simultaneously increases the flight safety of the aircraft. Because the auxiliary power device needs to provide auxiliary energy for aircraft ground maintenance, an air conditioning system, electronic equipment and the like, the operation time of the auxiliary power device is greatly prolonged, and the ratio of the working time of the auxiliary power device for civil aircraft to the flight time of the aircraft is about 0.85. Based on the above considerations, there is a continuing need for auxiliary power units that reduce fuel consumption rates.

The bleed air mode of the auxiliary power device in the prior art mainly comprises two modes of core compressor bleed air and load compressor bleed air.

However, since the auxiliary power unit generally adopts equal physical rotation speed control, for the auxiliary power unit for core compressor bleed air, the bleed air flow rate of the auxiliary power unit is highly coupled with the output electric power of the auxiliary power unit, the temperature before the turbine, the surge margin and the like. When bleed air parameters are changed, the operating conditions of the gas turbine starter need to be changed accordingly. The above situation brings inconvenience to the design and efficient operation of the auxiliary power unit.

Disclosure of Invention

Therefore, the technical problem to be solved by the invention is that in the prior art, as the auxiliary power device usually adopts equal physical rotation speed control, the bleed air flow of the auxiliary power device for the core compressor bleed air is highly coupled with the output electric power of the auxiliary power device, the temperature before the turbine, the surge margin and the like. When bleed air parameters are changed, the operating conditions of the gas turbine starter need to be changed accordingly. The above situation brings inconvenience to the design and efficient operation of the auxiliary power unit.

To this end, the invention provides a hybrid auxiliary power system for flexibly controlling the bleed air flow, comprising:

A gas turbine engine in communication with the duct for outputting bleed air;

A compressor in communication with the conduit for outputting bleed air, the compressor configured to deliver compressed air into the conduit to increase the bleed air flow;

A turbine in communication with the gas turbine engine through a duct to exhaust a portion of the air from the gas turbine engine.

Optionally, an air distributor is arranged between the turbine and the gas turbine engine, the compressor is communicated with the air distributor, and an air blender is arranged between the compressor and the air distributor, and the air blender is communicated with the output bleed air pipeline.

Optionally, a first generator is connected to and driven by the gas turbine engine to generate electricity.

Optionally, a second generator is connected with the turbine and driven by the turbine to generate electricity.

Optionally, the power type power generation device further comprises a power type battery electrically connected with the first generator and the second generator.

Optionally, the motor is electrically connected with the first generator, the second generator and the power type battery, and the motor is connected with the compressor to drive the compressor.

Optionally, the motor, the first generator, the second generator, and the power battery are electrically connected to each other through an electrical energy distributor.

Optionally, a controller is also included in electrical communication with the motor, the first generator, the second generator, the electrical energy distributor, the air distributor, and the air blender.

The hybrid auxiliary power system capable of flexibly controlling the air entraining flow has the following advantages:

The invention provides a hybrid auxiliary power system capable of flexibly controlling bleed air flow, which comprises a gas turbine engine, a compressor and a turbine, wherein the gas turbine engine is communicated with a pipeline for outputting bleed air, the compressor is communicated with the pipeline for outputting bleed air, and the compressor is configured to convey compressed air into the pipeline to increase the bleed air flow; a turbine is in communication with the gas turbine engine via a duct to exhaust a portion of the air from the gas turbine engine.

The hybrid auxiliary power system with the structure and the flexible control of the bleed air flow can be realized by using the same gas turbine starter for different auxiliary power system bleed air requirements of an airplane by introducing a compressor and a turbine, and only the working state of the compressor or the turbine needs to be changed. Since the compressor, turbine and gas turbine engine are decoupled, the operating state of the compressor can be conveniently changed without changing the operating state of the gas turbine engine.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic diagram of the operation of a compressor in a hybrid auxiliary power system that is provided in an embodiment of the present invention and that is capable of flexibly controlling bleed air flow;

FIG. 2 is a schematic view of the operation of a turbine in a hybrid auxiliary power system providing flexible control of bleed air flow in an embodiment of the invention;

FIG. 3 is a further operational schematic of a turbine in a hybrid auxiliary power system providing flexible control of bleed air flow in an embodiment of the invention;

FIG. 4 is a schematic illustration of a compressor and turbine combination into one system in a hybrid auxiliary power system that flexibly controls bleed air flow provided in an embodiment of the present invention;

FIG. 5 is a schematic diagram of the operation of a hybrid auxiliary power system (battery SOC in a high position) that is provided in an embodiment of the invention that flexibly controls bleed air flow;

FIG. 6 is a schematic diagram of the operation of a hybrid auxiliary power system (battery SOC in low) with flexible control of bleed air flow provided in an embodiment of the invention;

FIG. 7 is a schematic operational view of a hybrid auxiliary power system providing flexible control of bleed air flow in an embodiment of the invention (ground service condition);

FIG. 8 is a schematic operation of a hybrid auxiliary power system providing flexible control of bleed air flow in an embodiment of the invention (high altitude emergency operation when the gas turbine engine has not been fired);

Fig. 9 is a schematic diagram of the operation of a hybrid auxiliary power system (including a heat exchanger) that is provided in an embodiment of the invention that can flexibly control the bleed air flow.

Reference numerals illustrate:

1-a gas turbine engine;

a 2-compressor;

3-a turbine;

4-an air distributor;

5-an air blender;

6-a first generator;

7-a second generator;

8-power type battery;

9-an electric motor;

10-an electrical energy distributor;

11-a controller;

12-heat exchanger.

Detailed Description

The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.

Examples

For a typical auxiliary power unit having a primary engine start and providing a ring bleed air control, the operating time in the ring bleed air condition is much longer than the primary engine start condition operating time. The bleed air state of the auxiliary power unit can be determined by three physical parameters of bleed air temperature, bleed air pressure and bleed air flow.

Because of the limitation of the operating temperature of the aircraft pipeline system, the bleed air temperature usually has a relatively fixed maximum limit value, and in practice, the bleed air temperature of the auxiliary power unit is relatively stable in the whole envelope range when operating, and in the case of a certain auxiliary power unit, the whole envelope range of the bleed air temperature varies in the range around 450K.

The auxiliary power device air-entraining mode mainly comprises a core compressor air-entraining mode and a load compressor air-entraining mode. Because the auxiliary power device usually adopts equal physical rotation speed control, for the auxiliary power device for core compressor bleed air, the bleed air flow of the auxiliary power device is highly coupled with the output electric power of the auxiliary power device, the temperature before the turbine, the surge margin and the like.

For example: a typical working envelope of the auxiliary power unit is-40 ℃ to (ISA+37) DEG C, 0-10000 m. Because of the complex and varying demands of aircraft, auxiliary power units sometimes need to provide more electrical power alone (without providing high pressure bleed air), high flows of high pressure bleed air (with small amounts of electrical power), and relatively balanced electrical power and bleed air flows in order to meet the demands of aircraft under extreme conditions within the operating envelope. The more electric power the auxiliary power device provides, the smaller the surge margin of the auxiliary power device is, and the lower the temperature before the turbine is; the greater the bleed air flow provided, the greater its surge margin, but the higher the turbine front temperature (resulting in reduced reliability and overall life, increased design and manufacturing difficulties).

The bleed air flow of a single auxiliary power unit in a particular atmospheric environment has a maximum value (assuming M above which the auxiliary power unit exhaust temperature may exceed a limit value), the actual bleed air flow (not greater than the maximum value M) being generally determined by the aircraft requirements. Even with elaborate auxiliary power units, the maximum bleed air flow M of the auxiliary power unit varies considerably under different environmental conditions.

Even if the auxiliary power unit does not output bleed air, in order to prevent compressor surge, it is still necessary to bleed excess high-pressure gas through the anti-surge flaps, which likewise results in energy waste. The two conditions cause energy waste, and are not beneficial to reducing carbon emission.

The output power and bleed energy of the gas turbine engine can be regulated by the fueling rate, with the fuel consumption rate being the lowest when the gas turbine engine is operating at the design point (typically the maximum operating condition). Since the bleed air demand and the electrical power demand of an aircraft are in a dynamically changing process, this makes the conventional gas turbine auxiliary power unit deviate from the efficient design point for a large part of the time in an inefficient state.

To this end, the present embodiment provides a hybrid auxiliary power system that flexibly controls the bleed air flow, comprising a gas turbine engine 1, a compressor 2, a turbine 3, an air distributor 4, an air blender 5, a first generator 6, a second generator 7, a power cell 8, an electric motor 9, an electric energy distributor 10 and a controller 11.

In this embodiment, the bleed air system compressor 2 is schematically shown in operation in fig. 1, with a communication line between the gas turbine engine 1 and the compressor 2 and an air blender 5 connected between them, the air blender 5 being in communication with the line for the output bleed air. By introducing a motor-driven compressor 2, the compressor 2 compresses the external air via separate air inlets, and the air after the compressor 2 is mixed with bleed air from the gas turbine engine 1 and supplied to the aircraft jointly.

In this embodiment, the operation of the turbine 3 is schematically illustrated in fig. 2 and 3. As shown in fig. 2, the gas turbine engine 1 and the turbine 3 are in communication with a pipeline therebetween with an air distributor 4, the air distributor 4 also being in communication with the pipeline from which bleed air is output, in which case the auxiliary power unit converts surplus bleed air energy into electrical energy via the turbine 3, for example in the event of an electrical power shortage. As shown in fig. 3, the gas turbine engine 1 and the turbine 3 are in communication with a pipeline therebetween, and an air distributor 4 is arranged between them, the air distributor 4 also being in communication with the pipeline from which bleed air is output. Even if the aircraft does not have bleed air requirements, a large amount of high-pressure gas needs to be discharged through the anti-surge flaps in order to prevent engine surge, which would greatly reduce the economy, whereas in this embodiment by providing the turbine 3, excess bleed air can be converted into electrical energy.

In this embodiment, as shown in fig. 4, the compressor 2 and the turbine 3 are combined into one system, an air distributor 4 is arranged between the turbine 3 and the gas turbine engine 1 in a pipeline communicating with the two, the compressor 2 is communicated with the air distributor 4 in a pipeline communicating with the air mixer 5, and an air-entraining output pipeline is arranged between the two.

In this embodiment, as shown in fig. 5, when the aircraft bleed air flow demand is large, the maximum bleed air flow of the gas turbine engine 1 does not meet the demand (the higher the bleed air flow, the higher the gas turbine front temperature), the compressor 2 provides additional bleed air flow by compressing ambient air. In the normal mode, the battery remaining capacity SOC operation range is set to 30% -70%. Assuming that the battery remaining capacity SOC is approximately 70% at this time, the controller 11 supplies bleed air to the aircraft while supplying electric power to the aircraft in accordance with the demand signal of the aircraft control system and the SOC (remaining capacity) of the battery. The battery is discharged.

In the present embodiment, as shown in fig. 6, when the aircraft electrical power demand is large, the maximum electrical power of the gas turbine engine 1 does not meet the demand (the higher the electrical power, the smaller the surge margin), and the turbine 3 converts the additional bleed air flow into electrical energy. Assuming that the battery remaining capacity SOC is close to 30% at this time, the controller 11 generates electricity from the turbine 3 and discharges a part of bleed air of the gas turbine engine 1 to the atmosphere in accordance with the demand signal of the aircraft control system and the SOC (remaining capacity) of the battery, and the remaining part is directly supplied to the aircraft. The first generator 6 and the second generator 7 simultaneously supply electric power to the aircraft, and the battery is charged.

In this embodiment, as shown in fig. 7, when the aircraft is in a ground overhaul environment, there is no bleed air demand, and the gas turbine engine 1 is required to be anti-surge bleed air to prevent surge, excess bleed air energy is recovered by the turbine 3. In the normal mode, the battery remaining capacity SOC operation range is set to 30% -70%. Assuming that the battery remaining capacity SOC is 40% at this time, the controller 11 charges the battery according to the demand signal of the aircraft control system and the SOC (remaining capacity) of the battery.

In this embodiment, as shown in fig. 8, the aircraft is in an air flight phase, the main engine is stopped in the air, the auxiliary power system is required to provide emergency energy (the working time is short), and the remaining battery power SOC is in a high position. Since the gas turbine engine 1 requires a certain time in response to start-up, the controller 11 controls the compressor 2 to participate in operation according to a demand signal of an aircraft control system and the SOC (remaining capacity) of the battery, providing an emergency air source; the battery is discharged at this time, providing emergency power.

The motor 9 and the second generator 7 may be two motors, or the same motor having both the motor 9 and the generator functions may be selected (at this time, a clutch is required between the motor and the turbine 3 and the compressor 2, so as to ensure that the two motors do not affect each other during operation).

In other embodiments, as shown in fig. 9, another alternative use of the turbine 3 is to recover engine exhaust energy, the engine bleed air being heated in the engine high temperature exhaust before passing through the turbine 3 and then recovered as electrical energy by the turbine 3.

Compared with the existing auxiliary power device, the hybrid auxiliary power system capable of flexibly controlling the bleed air flow provided by the embodiment realizes flexible control of the bleed air flow, and decoupling is realized between the bleed air flow and the gas turbine engine 1. By introducing a power cell 8, a reservoir-like energy storage and release function can be achieved. The design constraints of the gas turbine auxiliary power plant are greatly reduced, and the gas turbine auxiliary power plant system has better economy under the same conditions.

By introducing one compressor 2 and one turbine 3, the different auxiliary power system bleed air requirements imposed on the aircraft can be achieved using the same gas turbine starter, only by changing the operating conditions of the compressor 2 or turbine 3. Since the compressor 2, the turbine 3 and the gas turbine engine 1 are decoupled, the operating state of the compressor 2 can be easily changed without changing the operating state of the gas turbine engine 1. When designing a new auxiliary power system, the design may be based on the selection of existing mature gas turbine engines 1.

It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.

Claims

1. A hybrid auxiliary power system for flexibly controlling bleed air flow, comprising:

A gas turbine engine (1) in communication with the conduit for outputting bleed air;

a compressor (2) in communication with the conduit for outputting bleed air, the compressor (2) being configured to deliver compressed air into the conduit to increase the bleed air flow;

-a turbine (3) in communication with the gas turbine engine (1) through a duct to exhaust part of the air of the gas turbine engine (1).

2. The hybrid auxiliary power system which can flexibly control the bleed air flow according to claim 1, characterized in that an air distributor (4) is arranged between the turbine (3) and the gas turbine engine (1), the compressor (2) is connected to the air distributor (4) and an air blender (5) is arranged between the two, and the air blender (5) is connected to the outgoing bleed air line.

3. The flexible bleed air flow controllable hybrid auxiliary power system as claimed in claim 2, further comprising a first generator (6) connected to the gas turbine engine (1) and driven by the gas turbine engine (1) for generating electricity.

4. A hybrid auxiliary power system capable of flexibly controlling the bleed air flow according to claim 3, further comprising a second generator (7) connected to the turbine (3) and driven by the turbine (3) to generate electricity.

5. The flexible, bleed air flow controllable hybrid auxiliary power system according to claim 4, further comprising a power battery (8) electrically connected to the first generator (6) and to the second generator (7).

6. The flexible, bleed air flow controllable hybrid auxiliary power system according to claim 5, further comprising an electric motor (9) electrically connected to the first generator (6), the second generator (7) and a power battery (8), and the electric motor (9) is connected to the compressor (2) for driving the compressor (2).

7. Hybrid auxiliary power system capable of flexibly controlling the bleed air flow according to claim 6, characterized in that the electric motor (9), the first generator (6), the second generator (7) and the power battery (8) are electrically connected to each other by means of an electric energy distributor (10).

8. The flexible, bleed air flow controllable hybrid auxiliary power system according to claim 7, further comprising a controller (11) in electrical signal connection with the electric motor (9), the first generator (6), the second generator (7), an electric energy distributor (10), an air distributor (4) and an air blender (5).