CN110821679B - Fuel oil supply system, fuel oil supply method and aircraft engine - Google Patents
Fuel oil supply system, fuel oil supply method and aircraft engine Download PDFInfo
- Publication number
- CN110821679B CN110821679B CN201810921857.5A CN201810921857A CN110821679B CN 110821679 B CN110821679 B CN 110821679B CN 201810921857 A CN201810921857 A CN 201810921857A CN 110821679 B CN110821679 B CN 110821679B
- Authority
- CN
- China
- Prior art keywords
- pressure
- fuel
- outlet
- oil
- inlet
- 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
- 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
- F02C7/236—Fuel delivery systems comprising two or more pumps
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention relates to a fuel oil supply system, a fuel oil supply method and an aircraft engine. The oil supply system comprises a jet pump, wherein the jet pump comprises a first inlet, a second inlet, a first outlet, a second outlet and an adjusting valve; the jet pump has a first working condition and a second working condition; the fuel input into the jet pump from the first inlet and the second inlet is output from the second outlet under the first working condition; under the second working condition, the fuel oil input into the jet pump from the first inlet and the second inlet is respectively output from the first outlet and the second outlet, and the opening degree of the first outlet is increased along with the increase of the pressure of the fuel oil entering from the first inlet by the regulating valve; and the fuel input from the second inlet is injected and pressurized by the fuel input from the first inlet and then is output from the second outlet. The fuel oil supply system, the fuel oil supply method and the aircraft engine at least have the advantages of stable operation, fuel oil temperature rise reduction and the like.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to a fuel oil supply system, a fuel oil supply method and an aircraft engine.
Background
The principle of a traditional aircraft engine fuel system is shown in figure 1, and the traditional aircraft engine fuel system mainly comprises a low-pressure pump 1, a high-pressure pump 2, a metering valve 3, a high-pressure shutoff valve 4, an oil return valve 5, a pressure difference valve 6, a fuel manifold 8, a fuel nozzle 7 and the like, wherein after fuel coming from an aircraft engine is extracted from an oil tank, the fuel is pressurized through the low-pressure pump 1 and the high-pressure pump 2, and the fuel enters the fuel manifold 8 and the fuel nozzle 7 through the metering valve 3 and the high-pressure shutoff valve 4 and is supplied to a combustion chamber of the aircraft engine. The metering valve 3 is used for metering the fuel quantity to the combustion chamber of the engine; the high-pressure shutoff valve 7 is used for keeping a fuel supply system to have enough minimum servo pressure and is timely shut off after the engine stops so as to cut off fuel to a combustion chamber of the engine; the differential pressure valve 6 is used for ensuring that the differential pressure between the front and the rear of the metering valve 3 is constant, and the fuel supply system is designed in such a way that the position of the metering valve 3 is controlled, so that the fuel quantity to a combustion chamber can be controlled. And the oil return valve 5 is used for returning the fuel oil which is provided by the high-pressure pump 2 and is required by the redundant engine to the low-pressure pump 1.
Because the high-pressure pump 2 mostly adopts a constant-displacement pump, and the rotating shaft of the high-pressure pump 2 and the high-pressure rotor are in gear transmission, the rotation speed regulation of the high-pressure pump 2 has certain hysteresis. Therefore, under some working conditions, for example, under the working conditions that the engine speed is high but the required fuel flow is small, a large amount of high-pressure fuel returns to the low-pressure pump 1 through the oil return valve 5, so that a series of problems of virtual hydraulic power consumption, temperature rise of a fuel system and the like are caused.
Therefore, in the prior art, as shown in fig. 2, there is an improvement that a jet pump 9 is arranged behind an oil return valve 5 of an oil return path in a fuel oil supply system, low-pressure fuel oil of a low-pressure pump 1 is input into the jet pump 9, high-pressure fuel oil output from the oil return valve 5 is input into the jet pump 9, and low-pressure fuel oil is injected and pressurized inside the jet pump 9, so that the pressure of the fuel oil output from the oil return valve 5 is fully utilized, and the hydraulic power utilization rate is improved. The fuel flow return position in the system is in front of the nozzle of the jet pump. However, in practical situations, the maximum value and the minimum value of the fuel demand of the aircraft engine are greatly different, under some working conditions, such as a high-speed low-flow point and some engine over-rotation cut-off points, the oil return valve 5 needs to return almost all the high-pressure fuel pressurized by the high-pressure pump 2, in this case, the pressure of the fuel system in a short time can be increased to a very high state, which is not favorable for unloading the fuel pump and has an influence on the service life of the fuel pump, and meanwhile, the range of the oil return flow is wide, and the matching design of the jet pump 9 and the fuel system is difficult, because the jet pump 9 itself has the limit pressure due to the limitation of materials, so in order to prevent the nozzle of the jet pump 9 from being damaged when the working condition that the pressure of the fuel system in the short time can be increased to a very high state occurs, the caliber of the jet pump 9 needs to be larger than, limiting its supercharging capacity.
In summary, there is a need in the art for a fuel supply system with good pressurization effect, low system temperature rise, and smooth operation.
Disclosure of Invention
An object of the present invention is to provide a fuel supply system.
It is an object of the present invention to provide an aircraft engine.
It is an object of the present invention to provide a method of supplying fuel.
The fuel oil supply system comprises an oil return way, wherein the oil return way comprises a jet pump, and the jet pump comprises a first inlet, a second inlet, a first outlet, a second outlet and an adjusting valve; the jet pump has a first working condition and a second working condition;
the fuel input into the jet pump from the first inlet and the second inlet is output from the second outlet under the first working condition;
under the second working condition, the fuel oil input into the jet pump from the first inlet and the second inlet is respectively output from the first outlet and the second outlet, and the opening degree of the first outlet is increased along with the increase of the pressure of the fuel oil entering from the first inlet by the regulating valve;
and the fuel input from the second inlet is injected and pressurized by the fuel input from the first inlet and then is output from the second outlet.
In an embodiment of the oil supply system, the regulating shutter comprises a spring structure located between the first outlet and the second inlet.
In an embodiment of the oil supply system, the first inlet input fuel comprises fuel returned by an oil return valve of the oil supply system, and the second inlet input fuel comprises fuel output by a low-pressure oil pump of the oil supply system.
In an embodiment of the oil supply system, the fuel output from the first outlet and the second outlet is output to a high-pressure oil pump of the oil supply system.
In an embodiment of the oil supply system, the regulating shutter comprises a pressure sensor and a slider.
According to a further aspect of the invention, an aircraft engine comprises a fuel supply system as described in any of the preceding.
A fuel supply method according to another aspect of the present invention includes:
inputting high-pressure fuel and low-pressure fuel into a jet pump;
in the first pressure section, all the high-pressure fuel oil is injected and pressurized to obtain low-pressure fuel oil, and the low-pressure fuel oil is output from the second outlet of the jet pump;
in the second pressure section, part of the high-pressure fuel is injected to pressurize the low-pressure fuel and is output to the jet pump from the second outlet, and part of the high-pressure fuel is directly output to the jet pump from the first outlet.
In an embodiment of the fuel supply method, in the second pressure section, the opening degree of the first outlet is increased along with the increase of the pressure of the high-pressure fuel so as to adjust the proportion of the high-pressure fuel for injecting the supercharged low-pressure fuel output and the direct output.
In an embodiment of the oil supply method, a regulating shutter comprising a spring structure is provided; when the pressure is increased from the first pressure section to the second pressure section, the pressure of the high-pressure fuel is increased to push the spring structure to open the first outlet of the jet pump through the regulating valve, and the opening degree of the first outlet is increased along with the increase of the pressure of the high-pressure fuel.
In summary, the advanced effects of the present invention at least include:
1. through the arrangement of the first outlet, part of high-pressure fuel can be directly output under the second working condition, and the limit pressure of the jet pump for injecting and pressurizing is controlled in a reasonable range, so that the caliber of the second outlet of the jet pump can be further reduced, the pressurizing capacity of the jet pump is enhanced, the problem that the caliber of the second outlet is limited to be above a certain range due to the consideration of overlarge limit pressure of the jet pump, the pressurizing capacity is limited, and the temperature rise of an aircraft engine fuel system is reduced;
2, unloading the fuel pump at high-speed small-flow points and some over-rotation fuel-cutting points of the aeroengine, and reducing fuel pressure fluctuation of a fuel system;
3. the aircraft engine adopting the oil supply system has stable operation and good fuel economy.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of a prior art fuel supply system for an aircraft engine.
Fig. 2 is a schematic view of another prior art arrangement of an aircraft engine fuel supply system.
Fig. 3 is a schematic structural diagram of an embodiment of the fuel supply system of the aircraft engine.
Fig. 4 is a graph comparing the pressurization capacity of the embodiment of the fuel supply system of the present application and the fuel supply system of fig. 2.
Fig. 5 is a graph comparing pressure fluctuations of the high-pressure pump fuel after an emergency stop of the engine in the embodiment of the fuel supply system of the present application and the fuel supply system of fig. 2.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
Further, it is to be understood that the positional or orientational relationships indicated by the directional terms such as "front, rear, upper, lower, left, right", "transverse, vertical, horizontal" and "top, bottom" and the like are generally based on the positional or orientational relationships shown in the drawings and are presented only for convenience in describing and simplifying the invention, and in the absence of a contrary explanation, these directional terms are not intended to indicate and imply that the referenced device or element must have a particular orientation or be constructed and operated in a particular orientation and therefore should not be construed as limiting the scope of the invention; the terms "inside" and "outside" refer to the inner and outer parts relative to the outline of each part itself, and the terms "first" and "second" are used to define the parts, and are used only for the convenience of distinguishing the corresponding parts, and the terms do not have any special meaning unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
Also, this application uses specific language to describe embodiments of the application. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "some embodiments" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
Referring to fig. 3, in some embodiments, the jet pump 9 of the oil return path of the oil supply system of the aircraft engine includes a first inlet 91, a second inlet 92, a first outlet 94, a second outlet 93, and a regulating flap 95. In the first operating condition of the jet pump 9, that is, when the pressure of the fuel output from the oil return valve 5 is low and the pressure of the fuel entering the jet pump 9 from the first inlet 91 is low, the regulating valve 95 is in the closed state at this time, and the pressure of the fuel entering from the first inlet 91 cannot make the regulating valve 95 open the first outlet 94, for example, in the embodiment of fig. 3, the regulating valve 95 includes a spring structure 96 located between the first outlet 94 and the second inlet 92, at this time, the displacement of the spring 96 pushed by the fuel entering from the first inlet 91 is insufficient to open the first outlet 94, at this time, all the fuel entering from the first inlet 91 performs injection pressurization on the low-pressure fuel entering from the second inlet 92 and output from the low-pressure pump 1, and after the injection pressurization, the fuel is output from the second outlet 93 to the high-pressure pump 2. In the second operating mode of the jet pump 9, in which the fuel pressure output from the return valve 5 is high, for example, at the high-speed low-flow point and at some engine over-rotation-cut points, the return valve 5 needs to return almost all of the high-pressure fuel pressurized by the high-pressure pump 2. At this time, the pressure of the fuel input from the oil return shutter 5 to the first inlet 91 is enough to push the regulating shutter 95 to open the first outlet 94, and the opening degree of the first outlet 94 is increased with the increase of the fuel pressure to increase the proportion of the fuel directly output from the first outlet 94, for example, in the embodiment of fig. 3, the regulating shutter 95 includes the spring structure 96 which is displaced to increase the opening degree of the first outlet 94 with the increase of the fuel pressure. It should be noted that the structure of the regulating valve for regulating the opening degree of the first outlet 94 is not limited to the spring structure 96 of fig. 3, and may be other structures, for example, a pressure sensor-slider (built-in micro motor) structure, when the pressure sensor senses a certain value, the micro motor is started to drive the slider to open the first outlet 94, and controls the micro motor to control the displacement of the slide block according to the sensed pressure value, further controls the opening degree of the first outlet 94, the structure of the regulating valve is not limited by the above introduction, the spring structure 96 has the advantages of simple mechanical structure, low cost, and the adoption of springs with different stiffness coefficients, the proportion of the oil output from the first outlet 94 and the second outlet 93 can be reasonably distributed according to different engine models, different requirements of power and oil quantity under the second working condition. Through the arrangement of the first outlet 94, the jet pump has the advantages that when the second working condition that the pressure of input fuel is higher is realized, part of high-pressure fuel can be directly output, the limit pressure of the jet pump 9 for injecting pressurization is controlled within a reasonable range, the caliber of the second outlet 93 of the jet pump 9, namely a nozzle, can be further reduced, the pressurization capacity of the jet pump 9 is enhanced, the limitation of the caliber of the second outlet 93 to be more than a certain range due to the consideration of the overlarge limit pressure of the jet pump 9 to limit the pressurization capacity is avoided, and the temperature rise of a fuel system of an aircraft engine is reduced. The specific technical effect is shown in fig. 4, wherein Q is the oil quantity output from the metering valve 3 to the combustion chamber, Q is the oil quantity of the return oil path from the return valve 5, the prior art scheme shown in fig. 2 is adopted, the relation between the fuel pressure delivered back to the high-pressure pump 2 and the return oil quantity is almost linear, and the scheme of the embodiment shown in fig. 3 is adopted, because the nozzle of the jet pump 9 can be set to be smaller, the supercharging capacity is stronger, when the return oil pressure is reduced, the pressure reduction output to the high-pressure pump 2 is obviously lower than the prior art scheme shown in fig. 2, the higher supercharging capacity is obtained under different return oil flow rates, and the temperature rise of the fuel system can be better reduced. Meanwhile, the fuel pressure is fully utilized, the waste of the pump pressure is reduced, and the fuel economy is further improved. In the range of Q from/Q back equal to 0-0.6, namely the pressure range with higher oil return pressure and large pressure change, the pressure of the scheme of the embodiment shown in figure 3 is reduced in a small range and the pressure is reduced more stably.
As shown in fig. 5, by adopting the scheme of the embodiment shown in fig. 3, compared with the pressure of the fuel system after the high-pressure pump 2 is stopped in emergency, the pressure of the prior art jet pump 9 shown in fig. 2 rises sharply after the emergency stop, the pressure rises sharply from 5MPa to more than 11MPa in the period of 2s, then the pressure falls from 11MPa to 3MPa in 4s along with the reduction of the engine speed, and the pressure rises and falls sharply in short time, which is obviously extremely disadvantageous for the service life and the working stability of the high-pressure pump 2. In the technical scheme of the embodiment shown in fig. 3, the pressure of the fuel system rises more smoothly after the emergency stop. In the time period of 1s, the pressure is only increased from 5MPa to 6MPa, then along with the decrease of the rotating speed of the engine, the pressure is decreased from 6MPa to 3MPa in 5s, the pressure increase and decrease are obviously more stable, the high-pressure pump 2 can work stably for a long time, and the engine can run stably.
As can be seen from the above description, the method for supplying fuel to a fuel system of an aircraft engine comprises:
inputting high-pressure fuel and low-pressure fuel into a jet pump 9;
in the first pressure section, all the high-pressure fuel is injected and pressurized to obtain low-pressure fuel, and the low-pressure fuel is output from the second outlet 93 to the jet pump 9;
in the second pressure stage, part of the high-pressure fuel is injected to pressurize the low-pressure fuel and is output from the second outlet 93 to the jet pump 9, and part of the high-pressure fuel is directly output from the first outlet 94 to the jet pump 9.
The first pressure section is smaller than the second pressure section, the first pressure section can be a stage with smaller return oil pressure, and the second pressure section is a stage with larger return oil pressure, such as high-rotating-speed small-flow points and engine over-rotation oil-cutting points.
In some embodiments, the method of adjusting the proportion of high pressure fuel output from the first and second outlets 94, 93 at the second pressure stage may include increasing the opening of the first outlet 94 with increasing pressure of the high pressure fuel to adjust the proportion of high pressure fuel used to inject the boosted low pressure fuel output to the direct output.
In some embodiments, the method of adjusting the opening degree of the first outlet 94 may include providing an adjustment shutter 95 including a spring structure 96; when the pressure rises from the first pressure section to the second pressure section, the pressure of the high-pressure fuel increases to push the spring structure 96 to open the first outlet 94 of the jet pump 9, and the opening degree of the first outlet 94 increases with the increase of the pressure of the high-pressure fuel.
While, for purposes of simplicity of explanation, the methodologies are shown and described as a series of acts, it is to be understood and appreciated that the steps are not limited by the order of acts, as some acts may, in accordance with one or more embodiments, occur in different orders and/or concurrently with other acts from that shown and described herein or not shown and described herein, as would be understood by one skilled in the art.
To sum up, the oil supply system, the oil supply method and the aircraft engine adopting the embodiment have the beneficial effects that at least:
1. through the arrangement of the first outlet, part of high-pressure fuel can be directly output under the second working condition, and the limit pressure of the jet pump for injecting and pressurizing is controlled in a reasonable range, so that the caliber of the second outlet of the jet pump can be further reduced, the pressurizing capacity of the jet pump is enhanced, the problem that the pressurizing capacity is limited because the caliber of the second outlet is limited to be above a certain range due to the consideration of overlarge limit pressure of the jet pump is avoided, the temperature rise of a fuel system of an aircraft engine is reduced,
2, unloading the fuel pump at high-speed small-flow points and some over-rotation fuel-cutting points of the aeroengine, and reducing fuel pressure fluctuation of a fuel system;
3. the aircraft engine adopting the oil supply system has stable operation and good fuel economy.
Although the present invention has been disclosed in the above-mentioned embodiments, it is not intended to limit the present invention, and those skilled in the art may make variations and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (8)
1. The utility model provides a fuel oil feeding system for aeroengine, includes the oil return oil circuit, the oil return oil circuit includes jet pump, its characterized in that:
the jet pump comprises a first inlet, a second inlet, a first outlet, a second outlet and an adjusting valve; the jet pump has a first working condition and a second working condition;
the fuel input into the jet pump from the first inlet and the second inlet is output from the second outlet under the first working condition;
under the second working condition, the fuel oil input into the jet pump from the first inlet and the second inlet is respectively output from the first outlet and the second outlet, and the opening degree of the first outlet is increased along with the increase of the pressure of the fuel oil entering from the first inlet by the regulating valve;
the fuel input from the second inlet is injected and pressurized by the fuel input from the first inlet and then is output from the second outlet; and the fuel oil output from the first outlet and the second outlet is output to a high-pressure oil pump of an oil supply system.
2. A fuel supply system as set forth in claim 1 wherein said regulator valve includes a spring structure located between said first outlet port and said second inlet port.
3. The fuel supply of claim 1, wherein said first inlet fuel comprises fuel returned from a return valve of the fuel supply and said second inlet fuel comprises fuel output from a low pressure pump of the fuel supply.
4. A fuel supply system as set forth in claim 1 wherein said regulating shutter includes a pressure sensor and a slider.
5. An aircraft engine comprising a fuel supply system as claimed in any one of claims 1 to 4.
6. A method of supplying fuel to an aircraft engine, comprising:
inputting high-pressure fuel and low-pressure fuel into a jet pump;
in the first pressure section, all the high-pressure fuel oil is injected and pressurized to obtain low-pressure fuel oil, and the low-pressure fuel oil is output from the second outlet to the high-pressure oil pump of the oil supply system;
in the second pressure section, part of the high-pressure fuel oil is injected and pressurized, and the low-pressure fuel oil is output from the second outlet to the jet pump, and part of the high-pressure fuel oil is directly output from the first outlet to the high-pressure oil pump of the oil supply system.
7. The method of claim 6, comprising:
in the second pressure section, the opening degree of the first outlet is increased along with the increase of the pressure of the high-pressure fuel oil so as to adjust the proportion of the high-pressure fuel oil for injecting the pressurized low-pressure fuel oil to be directly output.
8. The method of claim 7, comprising:
arranging an adjusting valve comprising a spring structure;
when the pressure is increased from the first pressure section to the second pressure section, the pressure of the high-pressure fuel is increased to push the spring structure to open the first outlet of the jet pump through the regulating valve, and the opening degree of the first outlet is increased along with the increase of the pressure of the high-pressure fuel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810921857.5A CN110821679B (en) | 2018-08-14 | 2018-08-14 | Fuel oil supply system, fuel oil supply method and aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810921857.5A CN110821679B (en) | 2018-08-14 | 2018-08-14 | Fuel oil supply system, fuel oil supply method and aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110821679A CN110821679A (en) | 2020-02-21 |
| CN110821679B true CN110821679B (en) | 2021-02-05 |
Family
ID=69547159
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810921857.5A Active CN110821679B (en) | 2018-08-14 | 2018-08-14 | Fuel oil supply system, fuel oil supply method and aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110821679B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111927637B (en) * | 2020-08-11 | 2023-05-23 | 中国航发北京航科发动机控制系统科技有限公司 | Fuel oil emergency oil supply mechanism and emergency oil supply method |
| CN112392605B (en) * | 2020-10-30 | 2023-10-20 | 中国航发西安动力控制科技有限公司 | Differential pressure mechanism |
| CN113217195A (en) * | 2021-06-28 | 2021-08-06 | 中科航星科技有限公司 | Aircraft engine fuel system |
| US20230358174A1 (en) * | 2022-05-06 | 2023-11-09 | Hamilton Sundstrand Corporation | Aircraft fuel pumping system |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6466500A (en) * | 1987-09-08 | 1989-03-13 | Nippon Denso Co | Jet pump for vehicle fuel supplier |
| JP4013022B2 (en) * | 2000-09-13 | 2007-11-28 | 日産自動車株式会社 | Jet pump |
| US20030136371A1 (en) * | 2001-08-09 | 2003-07-24 | David Killion | Energy efficient fluid pump system |
| US20080273992A1 (en) * | 2007-05-03 | 2008-11-06 | Metaldyne Company Llc. | Cavitation-deterring energy-efficient fluid pump system and method of operation |
| CN205689340U (en) * | 2016-06-21 | 2016-11-16 | 中航商用航空发动机有限责任公司 | Aero-engine parking jettison gear, oil supply system and aero-engine |
| CN108131335B (en) * | 2016-11-30 | 2019-09-17 | 中国航发商用航空发动机有限责任公司 | Aircraft engine fuel oil system and its larynx mouth are pumped away from variable-spray |
-
2018
- 2018-08-14 CN CN201810921857.5A patent/CN110821679B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110821679A (en) | 2020-02-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110821679B (en) | Fuel oil supply system, fuel oil supply method and aircraft engine | |
| JP5539525B2 (en) | Fuel supply circuit for aero engines | |
| US9091212B2 (en) | Fuel and actuation system for gas turbine engine | |
| CN101198784B (en) | Fuel injection system for an internal combustion engine | |
| US10502138B2 (en) | Dual pump fuel system with pump sharing connection | |
| US4884545A (en) | Fuel injection system for an internal combustion engine | |
| US7966995B2 (en) | Dual level pressurization control based on fuel flow to one or more gas turbine engine secondary fuel loads | |
| US9803638B2 (en) | Control circuit for transmission variable displacement pump with improved efficiency | |
| US9617923B2 (en) | Engine fuel control system | |
| CN210738696U (en) | Open-cycle variable-thrust liquid rocket engine system | |
| CN101896710B (en) | Fuel pressure regulating system | |
| CN102239325A (en) | Fuel delivery and control system including a variable displacement actuation pump supplementing a fixed displacement main pump | |
| US9453463B2 (en) | High efficiency, high pressure gas turbine engine fuel supply system | |
| CN102678338B (en) | Oil supply pressure regulating system for aircraft engine and regulating method thereof | |
| US10526973B2 (en) | System for supplying a turbine engine with fluid having a low pressure pumping assembly comprising two pumps in parallel | |
| JP2016503861A (en) | Dual pump / double bypass fuel pump system | |
| EP2479408B1 (en) | Aircraft engine fuel system | |
| CN108138657A (en) | Pass through the recycling of the fluid of turbine centrifugal pump | |
| CN109065913A (en) | It is a kind of to return hydrogen system for fuel cell hydrogen | |
| CN103821580A (en) | Variable control method and system for oil pump with variable displacement | |
| US6655123B2 (en) | Device for economizing fuel supply in a fuel supply circuit | |
| JP3910057B2 (en) | Two level pressurization valve controlled by fuel metering unit | |
| US3614269A (en) | Integrated pump-control system using a unitized pump | |
| CN205136174U (en) | Energy -saving constant pressure oil source system | |
| CN214188333U (en) | Hydraulic circuit of injection molding machine |
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 |