CN118323447A - Aircraft parallel combined engine system and control method thereof - Google Patents
Aircraft parallel combined engine system and control method thereof Download PDFInfo
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- CN118323447A CN118323447A CN202410360016.7A CN202410360016A CN118323447A CN 118323447 A CN118323447 A CN 118323447A CN 202410360016 A CN202410360016 A CN 202410360016A CN 118323447 A CN118323447 A CN 118323447A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The application belongs to the technical field of aircraft parallel combined engine design, and particularly relates to an aircraft parallel combined engine system and a control method thereof.
Description
Technical Field
The application belongs to the technical field of aircraft parallel combined engine design, and particularly relates to an aircraft parallel combined engine system and a control method thereof.
Background
The parallel combined engine is a hybrid engine combining a turbine engine and a ramjet engine, utilizes the advantages of different engines and meets the requirements of different flight phases.
The parallel combined engine, at low speed and take off stage, the turbine engine provides main thrust, through compressing and burning the mixture of air and fuel to produce thrust, the high thrust of the turbine engine can make the aircraft take off easily, at the flight stage above the medium speed, the ramjet takes over main thrust, utilize the air current compression and burning the mixture of air and fuel to produce thrust in the flight, the high efficiency of the ramjet can make the aircraft fly with lower fuel consumption.
The current parallel combined engine has the following defects:
1) In the low-speed flight stage, the parallel combined engine operates in a turbine engine working mode, the turbocharger provides air flow compression required by the air compressor to generate higher thrust, and in the high-speed flight stage, the parallel combined engine operates in a ramjet engine working mode, and air flow compression is provided by ramjet pressurization, but due to the limitation of aerodynamics and combustion processes, the thrust generation capacity is lower, so that the parallel combined engine gradually reduces the thrust along with the increase of the flight speed in a specific flight speed range, namely a thrust trap appears, which has important influence on the performance and the flight characteristics of the aircraft and needs to be overcome by complex optimization design and control strategies;
2) When the parallel combined engine carries out modal conversion along with the increase of the flying speed, the ramjet engine is gradually converted from a shut-down state to a high state, the turbine engine is gradually shut down from the high state, a certain period exists, the continuous and reliable operation of the auxiliary power system can not be ensured, and enough energy is provided for the aircraft;
3) When the aircraft flies at a high speed, a large amount of aerodynamic heat can be generated, the aircraft and the engine structure thereof are seriously influenced, currently, the aircraft and the engine structure thereof are thermally protected by fuel oil, the heat sink capability is limited, and the aircraft and the engine structure thereof are difficult to prevent from being thermally damaged.
The present application has been made in view of the above-described technical drawbacks.
Disclosure of Invention
It is an object of the present application to provide an aircraft parallel engine system and a method of operating the same that overcomes or alleviates at least one of the known technical drawbacks.
The technical scheme of the application is as follows:
One aspect provides an aircraft parallel engine system comprising a turbine engine, a ramjet engine, a liquid hydrogen fuel tank, an initial booster pump, a turbo pump, a turbine engine lubricating oil heat exchanger, a generator, an on-board heat exchanger, a heat exchanger in an air inlet channel of the turbine engine, and a fuel regulator;
the turbine engine and the ramjet engine are arranged in parallel;
The initial booster pump is connected with the liquid hydrogen fuel tank and the booster pump in the turbo pump, the booster pump in the turbo pump is connected with the turbine engine lubricating oil heat exchanger, the turbine engine lubricating oil heat exchanger is connected with the heat exchanger on the aircraft and the heat exchanger in the turbine engine air inlet channel, and a selection valve is arranged between the two heat exchangers;
the heat exchanger on the aircraft and the heat exchanger in the turbine engine air inlet channel are connected with an expansion turbine in a turbine pump, and the expansion turbine in the turbine pump is connected with a fuel regulator and is connected with a generator;
The fuel regulator is connected to the main combustion chamber, the afterburner and the ramjet combustion chamber of the turbine engine.
In another aspect, a method for controlling an aircraft parallel engine system is provided, which is used for controlling the aircraft parallel engine system, and includes:
In the stage of take-off, low-speed flight and climbing, controlling the ramjet engine to stop, pumping hydrogen fuel from a liquid hydrogen fuel tank by an initial booster pump, flowing to the booster pump in a turbine pump after boosting, flowing to a turbine engine lubricating oil heat exchanger after further boosting, further controlling flowing to the turbine engine air inlet channel heat exchanger by a selective valve, then flowing to an expansion turbine in the turbine pump to do work, driving the booster pump in the turbine pump to work, driving a generator to work, providing energy for an airplane, flowing to a fuel regulator, controlling flowing to a main combustion chamber and an afterburner of the turbine engine to burn, enabling the turbine engine to work, and generating thrust;
In the mode conversion stage, the turbine engine is controlled to be gradually changed from a high working state to a stop, the ramjet is gradually converted from the stop to the high working state, hydrogen fuel is extracted from a liquid hydrogen fuel tank by an initial booster pump, after the hydrogen fuel is pressurized, the hydrogen fuel flows to a booster pump in a turbopump, flows to a turbine engine lubricating oil heat exchanger after the hydrogen fuel is further pressurized, then the hydrogen fuel flows to a turbine engine air inlet passage heat exchanger and an aircraft heat exchanger by selecting a valve, and the hydrogen fuel flows to an expansion turbine in the turbopump from the turbine engine air inlet passage heat exchanger and the aircraft heat exchanger to do work so as to drive the booster pump in the turbopump to work and drive a generator to work so as to provide energy for the aircraft, and then the hydrogen fuel flows to a fuel regulator to control the main combustion chamber and the afterburner of the turbine engine to burn and the ramjet to burn so as to enable the turbine engine and the ramjet to work and generate thrust;
In medium-speed and high-speed flight stages, the turbine engine is controlled to stop, hydrogen fuel is pumped from a liquid hydrogen fuel tank by an initial booster pump, after being boosted, the hydrogen fuel flows to the booster pump in the turbine pump, after being further boosted, flows to the lubricating oil heat exchanger of the turbine engine, then flows to the expansion turbine in the turbine pump to do work by selecting a valve, drives the booster pump in the turbine pump to work, drives the generator to work, provides energy for the aircraft, and then flows to the fuel regulator to control the combustion of the combustion chamber of the ramjet engine, so that the ramjet engine works and thrust is generated.
According to at least one embodiment of the present application, in the method for controlling the parallel engine system of an aircraft, the mach number is 0-2 during the take-off, low-speed flight and climb phases.
According to at least one embodiment of the present application, in the method for controlling an aircraft parallel engine system, the mach number is 2-4 in the mode conversion stage.
According to at least one embodiment of the present application, in the method for controlling an aircraft parallel engine system, the mach number is greater than 4 during medium and high speed flight phases.
The application has at least the following beneficial technical effects:
The utility model provides an aircraft parallel combination engine system and control method thereof, design with liquid hydrogen as fuel, in the mode conversion stage, utilize hydrogen fuel gasification to reduce the air temperature that gets into turbine engine, so can make turbine engine's thrust keep great thrust between Mach 2-3, avoid producing thrust trap, and can be greater than 4 in the flight speed, utilize hydrogen fuel gasification to reduce aircraft structure temperature, avoid the aerodynamic heat under the high-speed flight state, damage aircraft structure, in addition, utilize the energy drive electricity generation of absorption and expansion process release of hydrogen fuel in whole flight section, guarantee the continuous reliable work of auxiliary power system, provide the energy for the aircraft, guarantee the safe flight of aircraft.
Drawings
FIG. 1 is a schematic illustration of an aircraft parallel engine system provided by an embodiment of the present application;
Wherein:
1-a turbine engine; 2-ramjet; a 3-hydrogen fuel tank; 4-an initial booster pump; 5-turbine pump; 6-a fuel regulator; 7-a turbine engine lubricating oil heat exchanger; an 8-generator; 9-an on-board heat exchanger; 10-heat exchanger in turbine engine.
For the purpose of better illustrating the embodiments, certain elements of the drawings are omitted, enlarged or reduced in size and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the application.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only a portion related to the present application is shown in the drawings, and other related portions may refer to a general design.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The words used in the description of the present application to indicate directions are merely used to indicate relative directions or positional relationships, and when the absolute position of the object to be described is changed, the relative positional relationship may be changed accordingly. As used in this description of the application, the word "comprising" or "comprises" does not exclude the presence of other elements or items listed after the word, and the like.
In addition, unless explicitly stated or limited otherwise, the terms "mounted," "connected," and the like as used in the description of the present application should be construed broadly, and may be, for example, fixed or removable; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate medium, and a person skilled in the art can understand the specific meaning in the present application according to the specific circumstances.
An aircraft parallel engine system is shown in fig. 1, and comprises a turbine engine 1, a ramjet engine 2, a liquid hydrogen fuel tank 3, an initial booster pump 4, a turbopump 5, a turbine engine lubricating oil heat exchanger 7, a generator 8, an aircraft heat exchanger 9, a turbine engine in-inlet heat exchanger 10 and a fuel regulator 6.
The turbine engine 1 and the ramjet engine 2 are arranged in parallel.
The initial booster pump 4 is connected with the liquid hydrogen fuel tank 3 and is connected with a booster pump in the turbopump 5, the booster pump in the turbopump 5 is connected with the turbine engine lubricating oil heat exchanger 7, the turbine engine lubricating oil heat exchanger 7 is connected with the on-board heat exchanger 9 and the turbine engine air inlet channel heat exchanger 10, and a selector valve is arranged between the two heat exchangers.
The heat exchanger 9 on the aircraft and the heat exchanger 10 in the air inlet of the turbine engine are connected with an expansion turbine in the turbine pump 5, and the expansion turbine in the turbine pump 5 is connected with the fuel regulator 6 and is connected with the generator 8.
The fuel regulator 6 is connected to the main combustion chamber, afterburner of the turbine engine 1 and to the combustion chamber of the ramjet engine 2, and is capable of metering, regulating and controlling the hydrogen fuel, and a plurality of selector valves are provided therein to enable control of the distribution of the hydrogen fuel among the main combustion chamber, afterburner and combustion chamber of the turbine engine 1 and the combustion chamber of the ramjet engine 2.
The aircraft parallel engine system disclosed in the above embodiment may be controlled according to the aircraft parallel engine system control method disclosed below.
1 In the stage of take-off, low-speed flight and climbing, mach number 0-2, controlling the ramjet engine to stop, pumping hydrogen fuel from a liquid hydrogen fuel tank 3 by an initial booster pump 4, after boosting, flowing to a booster pump in a turbopump 5, after further boosting, flowing to a turbine engine lubricating oil heat exchanger 7, radiating lubricating oil of the turbine engine 1, further controlling flowing to a turbine engine air inlet channel heat exchanger 10 by a selected valve, exchanging heat with air in the turbine engine 1 air inlet channel, flowing to an expansion turbine in the turbopump 5 to apply work, driving the booster pump in the turbopump 5 to work, driving a generator 8 to work, ensuring continuous and reliable work of an auxiliary power system, supplying energy for an airplane, flowing to a fuel regulator 6, controlling flowing to a main combustion chamber and an afterburner of the turbine engine 1 to burn, and enabling the turbine engine 1 to work to generate thrust.
2 In the mode conversion stage, mach number 2-4, the turbine engine 1 is controlled to be gradually changed from a high working state to a stop state, the ramjet engine 2 is gradually converted from the stop state to the high working state, the hydrogen fuel is initially pumped from the liquid hydrogen fuel tank 3 by the booster pump 4, after pressurization, the hydrogen fuel flows to the booster pump in the turbopump 5, after further pressurization, the hydrogen fuel flows to the turbine engine oil heat exchanger 7, heat dissipation is carried out on the lubricating oil of the turbine engine 1, further, the flow to the turbine engine air inlet channel heat exchanger 10 and the on-board heat exchanger 9 is controlled by a selective valve, the heat exchange with the air in the turbine engine 1 air inlet channel is gradually gasified, the heat exchange is carried out in the on-board heat exchanger 9 and the aircraft structure, the hydrogen fuel flowing out from the turbine engine air inlet channel heat exchanger 10 and the on-board heat exchanger 9 flows to the expansion turbine in the turbopump 5 to do work, the booster pump in the turbopump 5 is driven to work, the auxiliary power system is driven to work, the continuous and reliable work of the auxiliary power system is ensured, and then the auxiliary power system flows to the fuel regulator 6, the main combustion chamber and the afterburner of the turbine engine 1 are controlled to burn, the afterburner and the combustion chamber of the turbine engine 1 is gradually gasified, the air in the air inlet channel of the turbine engine 1 is subjected to heat exchange with the aircraft, the aircraft structure is subjected to work, and the ramjet engine 2 is driven to work, and the thrust is generated.
In the mode conversion stage, the turbine pump 5 continuously works, the working state of the turbine pump is not influenced by the change of the airflow of an engine air inlet passage, the electric energy can be continuously output through the generator 8, the continuous and reliable work of an auxiliary power system is ensured, energy is provided for an airplane, in addition, the heat exchanger 10 in the turbine engine air inlet passage utilizes hydrogen fuel to gasify and absorb heat, the heat sink capacity is large, the temperature of air entering the turbine engine 1 can be greatly reduced, the turbine engine 1 can normally work at a higher flying speed, mach numbers 2-3 can also generate larger thrust, a thrust trap is filled, the flying speed boundary of the turbine engine 1 can be greatly expanded, the minimum state point requirement of the work of the turbine engine 2 can be further improved, the design difficulty of the turbine engine is reduced, and the design efficiency of the turbine engine is improved.
3 In medium speed and high speed flight stage, mach number is greater than 4, control turbine engine shut down, with the hydrogen fuel of initial booster pump 4 extraction from liquid hydrogen fuel jar 3, after the pressure boost, flow to booster pump 5 in the turbopump, after further pressure boost, flow to turbine engine lubricating oil heat exchanger 7, dispel the heat to turbine engine 1 lubricating oil, and then control with the valve and flow to aircraft on heat exchanger 9, progressively gasify with the aircraft structure heat transfer, then flow to the expansion turbine in the turbopump 5 and do work, drive booster pump in the turbopump 5 work, and drive generator 8 work, guarantee the continuous reliable work of auxiliary power system, provide the energy for the aircraft, then flow to fuel regulator 6, control flow to ramjet engine 2 combustion chamber burns, make ramjet engine 2 work, produce thrust.
In the mode conversion stage, the on-board heat exchanger 9 utilizes hydrogen fuel gasification to absorb heat, has larger heat sink capacity, can effectively reduce the temperature of the aircraft structure, and avoids the damage to the aircraft structure due to aerodynamic heat in a high-speed flight state.
According to the aircraft parallel combined engine system and the control method thereof disclosed by the embodiment, liquid hydrogen is designed as fuel, and in the mode conversion stage, the temperature of air entering the turbine engine 1 is reduced by utilizing hydrogen fuel gasification, so that the thrust of the turbine engine 1 can keep larger thrust between Mach numbers 2-3, a thrust trap is avoided, and when the flight speed is higher than 4, the temperature of an aircraft structure is reduced by utilizing hydrogen fuel gasification, so that the aerodynamic heat in a high-speed flight state is avoided, the aircraft structure is prevented from being damaged, in addition, the energy released in the absorption and expansion processes of the hydrogen fuel is utilized to drive power generation in the whole flight section, the continuous and reliable work of an auxiliary power system is ensured, the energy is provided for the aircraft, and the safe flight of the aircraft is ensured.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.
Claims (5)
1. The aircraft parallel engine system is characterized by comprising a turbine engine (1), a ramjet engine (2), a liquid hydrogen fuel tank (3), an initial booster pump (4), a turbo pump (5), a turbine engine lubricating oil heat exchanger (7), a generator (8), an aircraft heat exchanger (9), a turbine engine air inlet channel inner heat exchanger (10) and a fuel regulator (6);
the turbine engine (1) and the ramjet engine (2) are arranged in parallel;
The initial booster pump (4) is connected with the liquid hydrogen fuel tank (3) and is connected with a booster pump in the turbine pump (5), the booster pump in the turbine pump (5) is connected with the turbine engine lubricating oil heat exchanger (7), the turbine engine lubricating oil heat exchanger (7) is connected with the heat exchanger (9) on the aircraft and the heat exchanger (10) in the turbine engine air inlet channel, and a selection valve is arranged between the two heat exchangers;
The heat exchanger (9) on the aircraft and the heat exchanger (10) in the turbine engine inlet channel are connected with an expansion turbine in the turbine pump (5), and the expansion turbine in the turbine pump (5) is connected with the fuel regulator (6) and is connected with the generator (8);
the fuel regulator (6) is connected with the main combustion chamber and the afterburner of the turbine engine (1) and the combustion chamber of the ramjet engine (2).
2. An aircraft parallel engine system steering method for steering an aircraft parallel engine system according to claim 1, comprising:
in the take-off, low-speed flight and climbing stages, controlling the ramjet engine to stop, pumping hydrogen fuel from a liquid hydrogen fuel tank (3) by an initial booster pump (4), after boosting, flowing to a booster pump in a turbine pump (5), after further boosting, flowing to a turbine engine lubricating oil heat exchanger (7), further controlling to flow to a heat exchanger (10) in an air inlet channel of the turbine engine by a selection valve, then flowing to an expansion turbine in the turbine pump (5) to do work, driving the booster pump in the turbine pump (5) to work, driving a generator (8) to work, providing energy for an airplane, and then flowing to a fuel regulator (6), controlling to flow to a main combustion chamber and an afterburner of the turbine engine (1) to burn, so that the turbine engine (1) works to generate thrust;
In the mode conversion stage, the turbine engine (1) is controlled to be gradually turned into a stop state from a high working state, the ramjet engine (2) is gradually turned into the high working state from the stop state, hydrogen fuel is pumped from a liquid hydrogen fuel tank (3) by an initial booster pump (4), after the booster pump is pressurized, the hydrogen fuel flows to a booster pump in a turbine pump (5), after the booster pump is further pressurized, the hydrogen fuel flows to a turbine engine lubricating oil heat exchanger (7), further a valve is selected to control the hydrogen fuel flowing to a turbine engine air inlet heat exchanger (10) and an aircraft heat exchanger (9), the hydrogen fuel flowing out of the turbine engine air inlet heat exchanger (10) and the aircraft heat exchanger (9) flows to an expansion turbine in the turbine pump (5) to do work, the booster pump in the turbine pump (5) is driven to work, and a generator (8) is driven to work, energy is provided for the aircraft, and then the hydrogen fuel flows to a fuel regulator (6), and the hydrogen fuel flows to a main combustion chamber and a afterburner of the turbine engine (1) is controlled to burn, and the ramjet engine (2) is burnt, so that the turbine engine (1) and the ramjet engine (2) work to generate thrust;
In medium-speed and high-speed flight phases, the turbine engine is controlled to stop, hydrogen fuel is pumped from a liquid hydrogen fuel tank (3) by an initial booster pump (4), after being boosted, the hydrogen fuel flows to a booster pump in a turbine pump (5), after being further boosted, flows to a turbine engine lubricating oil heat exchanger (7), then flows to an on-aircraft heat exchanger (9) by a selective valve control, then flows to an expansion turbine in the turbine pump (5) to do work, drives the booster pump in the turbine pump (5) to work, and drives a generator (8) to work, so as to provide energy for the aircraft, and then flows to a fuel regulator (6), and controls the combustion of the combustion chamber of the ramjet engine (2), so that the ramjet engine (2) works and generates thrust.
3. The method of operating an aircraft parallel engine system according to claim 2,
Mach numbers are 0-2 during take-off, low speed flight and climb phases.
4. The method of operating an aircraft parallel engine system according to claim 2,
In the mode conversion stage, mach number is 2-4.
5. The method of operating an aircraft parallel engine system according to claim 4,
Mach numbers are greater than 4 during medium and high speed flight phases.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410360016.7A CN118323447A (en) | 2024-03-27 | 2024-03-27 | Aircraft parallel combined engine system and control method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410360016.7A CN118323447A (en) | 2024-03-27 | 2024-03-27 | Aircraft parallel combined engine system and control method thereof |
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| CN118323447A true CN118323447A (en) | 2024-07-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202410360016.7A Pending CN118323447A (en) | 2024-03-27 | 2024-03-27 | Aircraft parallel combined engine system and control method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119267031A (en) * | 2024-09-29 | 2025-01-07 | 中国航发沈阳发动机研究所 | A parallel TBCC engine fuel supply system and control method thereof |
-
2024
- 2024-03-27 CN CN202410360016.7A patent/CN118323447A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119267031A (en) * | 2024-09-29 | 2025-01-07 | 中国航发沈阳发动机研究所 | A parallel TBCC engine fuel supply system and control method thereof |
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