CN111734530B - Redundancy electric fuel system and control method - Google Patents
Redundancy electric fuel system and control method Download PDFInfo
- Publication number
- CN111734530B CN111734530B CN202010569034.8A CN202010569034A CN111734530B CN 111734530 B CN111734530 B CN 111734530B CN 202010569034 A CN202010569034 A CN 202010569034A CN 111734530 B CN111734530 B CN 111734530B
- Authority
- CN
- China
- Prior art keywords
- fuel
- full
- control unit
- fuel pump
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
Abstract
The invention discloses a redundant electric fuel oil system and a control method, and belongs to the technical field of turbine engines. In the electrical fuel system with redundancy and the control method, a motor of the fuel pump is controlled by a full authority digital control unit to drive the fuel pump, and fuel in the fuel pump is extracted to supply fuel to an engine; the working state of the full-authority digital control unit is monitored by the first controller, when the full-authority digital control unit is in an abnormal state, the first controller controls the fuel regulating engine to provide power for the fuel pump motor, controls the fuel pump motor to drive the fuel pump, and pumps fuel oil in the fuel tank to supply the fuel oil to the engine, so that the redundancy and reliability of the redundant electric fuel oil system are greatly improved.
Description
Technical Field
The invention relates to the technical field of turbine engines, in particular to an electrical fuel system with redundancy and a control method.
Background
In order to ensure the normal operation of the aircraft and the engine, a fuel system is adopted to supply and adjust fuel required by the engine under various working conditions and states so as to ensure the safe and reliable operation of the engine and give full play to the performance. The traditional small aircraft engine fuel system mainly comprises a fuel pump connected to an accessory gear, a fuel adjusting part, a switching solenoid valve, an oil filter and the like. The fuel oil which is provided by the airplane and is pre-pressurized is pressurized by the fuel oil pump, then is metered by the fuel oil adjusting part and enters the combustion chamber for combustion.
For an engine, an engine fuel system, particularly a fuel adjusting part is very important, and the fuel adjusting part is used as an executing part of engine fuel control, receives an instruction from a full authority digital control unit (FADEC), and controls a fuel metering component to accurately supply fuel according to flight conditions, an accelerator instruction and the like. Generally, the fuel regulation section mainly includes a mechanical hydraulic unit (HMU) and a Fuel Metering Valve (FMV). The mechanical hydraulic assembly is used for converting an electric signal transmitted by the electronic control assembly of the engine into a hydraulic signal to drive various action parts; the fuel metering valve ensures accurate fuel entry into the combustion chamber.
The main defects of each part in the traditional small aircraft engine fuel system in the practical application process are as follows: because the fuel pump is limited by the fixed rotating speed ratio connected with the main shaft of the engine, after the fuel flow requirements of various states are met, a large redundancy design is often needed, so that the fuel pump is overlarge and overweight; the valve of the existing small-sized aircraft engine fuel system is realized through a mechanical hydraulic assembly, the size of components is small, the precision degree is high, the structure is complex, and the problems of slowness, clamping stagnation, failure and the like are easily caused by pollution. Therefore, how to solve the problem that the fuel system can meet the design requirement for accurate fuel supply and ensure the high stability and reliability of the fuel system is a technical problem to be solved urgently by technical personnel in the field.
Disclosure of Invention
In order to solve the problems, the electric fuel oil system and the control method aim at high stability, high reliability and high design precision redundancy.
The invention provides a redundant electric fuel oil system, comprising:
an engine;
the fuel pump is connected with the fuel tank through a through hole in the gear box of the engine and used for extracting fuel in the fuel tank;
the fuel pump motor is coaxially connected with the fuel pump and used for driving the fuel pump to supply oil to the engine;
the fuel regulating generator is arranged on a gear box of the engine, is coaxially connected with the engine and is arranged at the same side of the fuel pump, and is also connected with the fuel pump motor;
the full-authority digital control unit is connected with the fuel pump motor and used for controlling the fuel pump motor to drive the fuel pump;
the first controller is installed on the fuel adjusting generator, connected with the full-authority digital control unit and used for monitoring the working state of the full-authority digital control unit and controlling the fuel adjusting generator to supply power to the fuel pump motor.
Preferably, the method further comprises the following steps:
and the electromagnetic valve is arranged between the fuel pump and the engine and is used for carrying out on-off control on the flow flowing into the engine.
Preferably, the method further comprises the following steps:
the starting generator is coaxially connected with the engine and used for supplying power to the full-authority digital control unit;
the second controller is respectively connected with the starting generator and the full-authority digital control unit and is used for controlling the starting generator to supply power to the full-authority digital control unit;
the full-authority digital control unit is also used for monitoring the working state of the second controller.
Preferably, the method further comprises the following steps:
and the power supply is respectively connected with the full-authority digital control unit and the second controller and is used for supplying power to the full-authority digital control unit.
Preferably, the fuel regulating generator and the fuel pump motor are cooled by fuel oil.
The invention also provides a redundancy electric fuel oil control method, which is applied to the redundancy electric fuel oil system and comprises the following steps:
the full-authority digital control unit controls the fuel pump motor to drive the fuel pump, and extracts fuel oil in the fuel pump to supply the fuel oil to the engine;
the working state of the full-authority digital control unit is monitored through the first controller, and when the full-authority digital control unit is in an abnormal state, the first controller controls the motor of the fuel pump to drive the fuel pump, so that fuel in the fuel pump is extracted to supply fuel to the engine.
Preferably, the method comprises the following steps:
the second controller controls the starting generator to supply power to the power supply and the full-authority digital control unit;
and the full-authority digital control unit monitors the working state of the second controller, and controls the power supply to supply power to the engine when the second controller is in an abnormal state.
The beneficial effects of the above technical scheme are that:
in the technical scheme, in the redundant electric fuel system and the control method, a full-authority digital control unit controls a fuel pump motor to drive a fuel pump, and fuel in the fuel pump is extracted to supply fuel to an engine; the working state of the full-authority digital control unit is monitored by the first controller, when the full-authority digital control unit is in an abnormal state, the first controller controls the fuel regulating engine to provide power for the fuel pump motor, controls the fuel pump motor to drive the fuel pump, and pumps fuel oil in the fuel tank to supply the fuel oil to the engine, so that the redundancy and reliability of the redundant electric fuel oil system are greatly improved.
Drawings
FIG. 1 is a block diagram of one embodiment of a redundant electrical fuel system according to the present invention;
FIG. 2 is a schematic diagram of a hardware configuration of an embodiment of the electrical fuel system of the redundancy of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting.
As shown in fig. 1 and 2, the redundant electrical fuel system according to the present embodiment may be applied to an aircraft, and includes: the fuel pump 5, the fuel pump motor 3, the engine 1, the full-authority digital control unit 10, the fuel regulation generator 8 and the first controller 11;
the fuel pump 5 is connected with the fuel tank 4 through a through hole on the gear box 12 of the engine 1 and used for extracting fuel in the fuel tank 4;
it should be noted that: the gearbox 12 is an accessory gearbox and is a part of the engine 1. The fuel pump 5 may be provided with a safety valve to avoid damage to the pump due to excessive fuel pressure.
The fuel pump motor 3 is coaxially connected with the fuel pump 5 and is used for driving the fuel pump 5 to supply oil to the engine 1;
the fuel adjusting generator 8 is arranged on a gear box 12 of the engine 1, is coaxially connected with the engine 1 and is arranged at the same side of the fuel pump 5, the fuel adjusting generator 8 is also connected with the fuel pump motor 3, and the engine 1 is used for driving the fuel adjusting generator 8 to supply power to the fuel pump motor 3;
the full-authority digital control unit 10 is connected with the fuel pump motor 3 and is used for controlling the fuel pump motor 3 to drive the fuel pump 5;
and the first controller 11 is arranged on the fuel adjusting generator 8, is connected with the full-authority digital control unit 10, and is used for monitoring the working state of the full-authority digital control unit 10 and controlling the fuel adjusting generator 8 to supply power to the fuel pump motor 3.
In practical application, when the full-authority digital control unit 10 is in an abnormal state, the fuel regulation generator 8 mounted on the gear box 12 transmits a power supply signal to the first controller 11, the power supply signal and the control signal are provided to the fuel pump motor 3 after being processed by the first controller 11, and the fuel pump motor 3 drives the fuel pump 5 to supply fuel to the engine 1 according to the control signal; an aircraft throttle lever signal may be sent to the fuel pump motor 3 via the first controller 11 for control.
In the embodiment, under the normal condition, the full authority digital control unit 10 controls the fuel pump motor 3 to drive the fuel pump 5, and the fuel in the fuel tank 4 is extracted to supply the fuel to the engine 1; the operating state of the full authority digital control unit 10 is monitored using the first controller 11. When the full-authority digital control unit 10 is in an abnormal state (namely, the full-authority digital control unit 10 fails to work normally), the first controller 11 controls the fuel pump motor 3 to drive the fuel pump 5, and fuel in the fuel tank 4 is extracted to supply fuel to the engine 1, so that the redundancy and reliability of the redundant electric fuel system are greatly improved.
The electrical fuel oil system of this technical scheme's redundancy adopts fuel pump 5 to extract the fuel from oil tank 4, need not to adopt the valve that comprises mechanical hydraulic component, and fuel pump 5 is strong to the compressive capacity of pollutant for the valve, and simple structure can effectually avoid circumstances such as slow, jamming, inefficacy.
In a preferred embodiment, it may further include:
and an electromagnetic valve 2 installed between the fuel pump 5 and the engine 1, for on-off controlling a flow rate flowing into the engine 1.
In the present embodiment, the solenoid valve 2 is provided between the fuel pump 5 and the nozzle of the engine 1 to control fuel cut-off. In a preferred embodiment, it may further include:
the starting generator 6 is coaxially connected with the engine 1 and used for supplying power to the full authority digital control unit 10;
the second controller 9 is respectively connected with the starter generator 6 and the full-authority digital control unit 10, and is used for controlling the starter generator 6 to supply power to the full-authority digital control unit 10;
the full-authority digital control unit 10 is also used for monitoring the working state of the second controller 9.
In the embodiment, the starter generator 6 is used for supplying power to the engine 1 and the full-authority digital control unit 10, a control signal can be provided to the full-authority digital control unit 10 through an aircraft accelerator, the full-authority digital control unit 10 outputs a power supply signal and the control signal, and the fuel pump motor 3 is controlled to drive the fuel pump 5 to pump fuel out of the fuel tank 4 and supply the fuel to the engine 1 through the electromagnetic valve 2.
In a preferred embodiment, it may further include:
and the power supply 7 is respectively connected with the full-authority digital control unit 10 and the second controller 9 and is used for supplying power to the full-authority digital control unit 10.
Wherein the power supply 7 is an aircraft power supply.
In this embodiment, the full-authority digital control unit 10 is used to monitor the operating status of the second controller 9, and when the starter 6 or the second controller 9 fails, the power supply 7 can be used as a backup power supply to supply power to the full-authority digital control unit 10, so as to maintain the requirement of normal power consumption of the fuel pump motor 3.
The working state of the full authority digital control unit 10 is monitored through the first controller 11, and when the power supply 7 fails to supply power to the full authority digital control unit 10 or the full authority digital control unit 10 fails, the first controller 11 can control the fuel regulation generator 8 to supply power to the fuel pump motor 3 so as to maintain the normal power consumption requirement of the fuel pump 5.
In the preferred embodiment, the fuel trim generator 8 and the fuel pump motor 3 are fuel cooled. The fuel pump motor 3 is connected with the fuel tank 4, and the fuel pump motor 3 is cooled through fuel.
The existing mechanical cooling generally needs engine oil for cooling, an additional oil way is needed, the structure is relatively complex, and two types of oil, namely fuel oil and lubricating oil, are involved. In this embodiment, adopt the fuel to cool off, utilize the fuel among the fuel feeding process to cool off fuel pump 5 and fuel generator 8, for the rear end fuel feeding simultaneously, simple structure saves space, and the practicality is strong and has improved the radiating efficiency.
The redundancy electric fuel system provided by the invention is characterized in that a starting generator 6 provides a power supply signal for the starting generator 6 under a general condition, and an airplane throttle lever provides a control signal for a full-authority digital control unit 10; when the starting generator 6 or the second controller 9 fails, the power supply 7 serves as a backup power supply.
When the power supply 7 fails, the fuel regulating generator 8 and the first controller 11 are used as backup power supplies, wherein the fuel regulating generator 8 can be replaced on a gear box which is attached to the engine 1 in situ, and fuel oil cooling is adopted together with the fuel pump motor 3.
When the full authority digital control unit 10 fails, the first controller 11 serves as a backup power source and receives a control signal sent by an airplane throttle stick. The fuel pump 5, the fuel pump motor 3, the first controller 11 and the electromagnetic valve 2 form a minimum fuel system, can meet the full-state fuel requirement of the engine 1, and provide power required by the cruise, idling and landing of the airplane. The fuel oil system has the advantages of novel and simple structure, convenience in use, strong reliability and capability of in-situ interchange. Has good popularization and application value.
Referring to fig. 1 and 2, the present invention further provides a redundancy electric fuel control method, applied to the redundancy electric fuel system, including:
the full-authority digital control unit 10 controls the fuel pump motor 3 to drive the fuel pump 5, and pumps the fuel in the fuel tank 4 to supply the fuel to the engine 1;
the working state of the full authority digital control unit 10 is monitored through the first controller 11, and when the full authority digital control unit 10 is in an abnormal state, the first controller 11 controls the fuel pump motor 3 to drive the fuel pump 5, and fuel in the fuel tank 4 is extracted to supply fuel to the engine 1.
In the embodiment, the redundant electric fuel control method controls the fuel pump motor 3 to drive the fuel pump 5 through the full authority digital control unit 10, extracts fuel in the fuel tank 4 and supplies the fuel to the engine 1; the working state of the full-authority digital control unit 10 is monitored by the first controller 11, when the full-authority digital control unit 10 is in an abnormal state, the first controller 11 controls the fuel pump motor 3 to drive the fuel pump 5, and fuel in the fuel tank 4 is extracted to supply fuel to the engine 1, so that the redundancy and reliability of the redundant electric fuel system are greatly improved, and meanwhile, compared with the structure of the traditional engine 1 fuel system, the redundant electric fuel system can more accurately control the fuel supply amount, and the adopted fuel pump 5 is small in size and light in weight.
In a preferred embodiment, comprising:
the second controller 9 controls the starter generator 6 to supply power to the power supply 7 and the full authority digital control unit 10;
the full-authority digital control unit 10 monitors the working state of the second controller 9, and when the second controller 9 is in an abnormal state, the full-authority digital control unit 10 controls the power supply 7 to supply power to the engine 1.
In the electrical fuel control method of redundancy provided by the invention, a generator 6 provides a power supply signal to a full-authority control unit 10 under a general condition, and an airplane throttle lever provides a control signal to the full-authority digital control unit 10; when the starting generator 6 or the second controller 9 fails, the power supply 7 serves as a backup power supply.
When the power supply 7 fails, the fuel regulating generator 8 and the first controller 11 are used as backup power supplies, wherein the fuel regulating generator 8 can be replaced on a gear box which is attached to the engine 1 in situ, and fuel oil cooling is adopted together with the fuel pump motor 3.
When the full authority digital control unit 10 fails, the first controller 11 receives a control signal transmitted from the aircraft throttle lever as a backup. The fuel pump 5, the fuel pump motor 3, the first controller 11 and the electromagnetic valve 2 form a minimum fuel system, can meet the full-state fuel requirement of the engine 1, and provide power required by the cruise, idling and landing of the airplane. The fuel oil system has the advantages of novel and simple structure, convenience in use, strong reliability and capability of in-situ interchange. Has good popularization and application value.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention.
Claims (5)
1. An electrical fuel system with redundancy, comprising:
an engine;
the fuel pump is connected with the fuel tank through a through hole in the gear box of the engine and used for extracting fuel in the fuel tank;
the fuel pump motor is coaxially connected with the fuel pump and used for driving the fuel pump to supply oil to the engine;
the fuel regulating generator is arranged on a gear box of the engine, is coaxially connected with the engine and is arranged at the same side of the fuel pump, and is also connected with the fuel pump motor;
the full-authority digital control unit is connected with the fuel pump motor and used for controlling the fuel pump motor to drive the fuel pump;
the starting generator is coaxially connected with the engine and used for supplying power to the full-authority digital control unit;
the first controller is arranged on the fuel adjusting generator, is connected with the full-authority digital control unit, monitors the working state of the full-authority digital control unit and controls the fuel adjusting generator to supply power for the fuel pump motor; when the full-authority digital control unit is in an abnormal state, the first controller controls the fuel regulating engine to provide power for the fuel pump motor, controls the fuel pump motor to drive the fuel pump, and extracts fuel in the fuel tank to supply the fuel to the engine;
the second controller is respectively connected with the starting generator and the full-authority digital control unit and is used for controlling the starting generator to supply power to the full-authority digital control unit; the full-authority digital control unit is also used for monitoring the working state of the second controller; when the second controller is in an abnormal state, the full-authority digital control unit controls the power supply to supply power to the engine.
2. The electrical redundancy fuel system according to claim 1, further comprising:
and the electromagnetic valve is arranged between the fuel pump and the engine and is used for carrying out on-off control on the flow flowing into the engine.
3. The electrical redundancy fuel system according to claim 1, further comprising:
and the power supply is respectively connected with the full-authority digital control unit and the second controller and is used for supplying power to the full-authority digital control unit.
4. The redundant electrical fuel system of claim 1, wherein the fuel trim generator and the fuel pump motor are fuel cooled.
5. A redundant electrical fuel control method applied to the redundant electrical fuel system according to claim 1, comprising:
the full-authority digital control unit controls the fuel pump motor to drive the fuel pump, and extracts fuel oil in the fuel pump to supply the fuel oil to the engine;
monitoring the working state of the full-authority digital control unit through the first controller, and controlling the fuel pump motor to drive the fuel pump and extract fuel in the fuel tank to supply fuel to the engine when the full-authority digital control unit is in an abnormal state;
the second controller controls the starting generator to supply power to the power supply and the full-authority digital control unit;
and the full-authority digital control unit monitors the working state of the second controller, and controls the power supply to supply power to the engine when the second controller is in an abnormal state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010569034.8A CN111734530B (en) | 2020-06-19 | 2020-06-19 | Redundancy electric fuel system and control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010569034.8A CN111734530B (en) | 2020-06-19 | 2020-06-19 | Redundancy electric fuel system and control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111734530A CN111734530A (en) | 2020-10-02 |
| CN111734530B true CN111734530B (en) | 2021-04-06 |
Family
ID=72651914
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010569034.8A Active CN111734530B (en) | 2020-06-19 | 2020-06-19 | Redundancy electric fuel system and control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111734530B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112379588B (en) * | 2020-11-27 | 2021-10-22 | 上海尚实能源科技有限公司 | Fuel regulation control system of double-margin aircraft engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101438039A (en) * | 2006-05-18 | 2009-05-20 | Mtu飞机发动机有限公司 | Modular fuel supply device for a gas turbine |
| CN104763534A (en) * | 2015-02-06 | 2015-07-08 | 中国人民解放军空军工程大学 | Modular combined electric fuel supply and control system |
| CN108603444A (en) * | 2016-01-29 | 2018-09-28 | 赛峰动力设备公司 | The electronic control system of partial redundance |
| CN110460149A (en) * | 2019-09-25 | 2019-11-15 | 江苏恒军动力科技有限公司 | One kind is novel to use miniature gas turbine as mobile generator system |
-
2020
- 2020-06-19 CN CN202010569034.8A patent/CN111734530B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101438039A (en) * | 2006-05-18 | 2009-05-20 | Mtu飞机发动机有限公司 | Modular fuel supply device for a gas turbine |
| CN104763534A (en) * | 2015-02-06 | 2015-07-08 | 中国人民解放军空军工程大学 | Modular combined electric fuel supply and control system |
| CN108603444A (en) * | 2016-01-29 | 2018-09-28 | 赛峰动力设备公司 | The electronic control system of partial redundance |
| CN110460149A (en) * | 2019-09-25 | 2019-11-15 | 江苏恒军动力科技有限公司 | One kind is novel to use miniature gas turbine as mobile generator system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111734530A (en) | 2020-10-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7118336B2 (en) | Pressurized oil supply for propeller engine system | |
| EP1726879B1 (en) | Reduced-weight fuel system for a gas turbine engine, gas turbine engine including such a system, and method of providing fuel to such a gas turbine engine | |
| EP2987961B1 (en) | Gas turbine engine system and corresponding method | |
| JP6609566B2 (en) | Method for supporting a turboshaft engine in a stand-by state of a multi-engine helicopter, and architecture of a propulsion system for a helicopter comprising at least one turboshaft engine capable of entering a stand-by state | |
| RU2352800C2 (en) | Method and system to generate power to drive engine auxiliary components | |
| EP0474585B1 (en) | A dual pump improved fuel delivery system | |
| US20100132365A1 (en) | Start-Up Control For a Compact Lightweight Turbine | |
| US7681402B2 (en) | Aeroengine oil tank fire protection system | |
| EP2133537A2 (en) | Bi-modal air turbine starter assembly | |
| US8093747B2 (en) | Aircraft electrical power system architecture using auxiliary power unit during approach and taxi | |
| US10890112B2 (en) | Method of increasing the safety of a power plant, and a power plant suitable for implementing the method | |
| GB2455901A (en) | An auxiliary circuit operating actuators and having a dedicated pump suitable for turbomachinery | |
| RU2687469C2 (en) | Gas turbine engine, twin-engine helicopter equipped with such gas-turbine engine, and optimization method of super-low gas mode with zero power of such two-engine helicopter | |
| KR20130099024A (en) | Method for optimizing the operability of an aircraft propulsive unit, and self-contained power unit for implementing same | |
| EP1743092B1 (en) | Two-displacement setting variable displacement pump used as engine over-thrust protection with fuel system thermal benefit | |
| CN111734530B (en) | Redundancy electric fuel system and control method | |
| CN114837814B (en) | Thermal management type combined power device | |
| US5277020A (en) | Hydraulically actuated aircraft engine control system | |
| CN102575972A (en) | Non-flame-out test for the combustion chamber of a turbine engine | |
| CA3078274C (en) | Method for creating a required pressure and fuel flow rate in a fuel system of a gas turbine engine | |
| CN108035829A (en) | A kind of airliner engine fuel control unit | |
| RU2329387C2 (en) | Gas turbine engine fuel feed system | |
| CN117157454A (en) | System for pumping and metering fluid for turbine engine and method for controlling the same | |
| Yang et al. | Design and Verification of Full Authority Digital Electronic Control System for APU | |
| POWER | 3. iIlil |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 201611 3 3 Ting Ting Road, Che Dun Town, Songjiang District, Shanghai Patentee after: Shanghai Shangshi aeroengine Co.,Ltd. Address before: 201611 3 3 Ting Ting Road, Che Dun Town, Songjiang District, Shanghai Patentee before: SHANGHAI SHANGSHI ENERGY TECHNOLOGY CO.,LTD. |
|
| CP01 | Change in the name or title of a patent holder |