CN110541849A - Oil return ejector and aircraft engine fuel system comprising same - Google Patents
Oil return ejector and aircraft engine fuel system comprising same Download PDFInfo
- Publication number
- CN110541849A CN110541849A CN201810530735.3A CN201810530735A CN110541849A CN 110541849 A CN110541849 A CN 110541849A CN 201810530735 A CN201810530735 A CN 201810530735A CN 110541849 A CN110541849 A CN 110541849A
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- China
- Prior art keywords
- nozzle
- oil return
- oil
- shell
- outer end
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- 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.)
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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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/14—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid
- F04F5/24—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid displacing liquids, e.g. containing solids, or liquids and elastic fluids
- F04F5/28—Restarting of inducing action
- F04F5/30—Restarting of inducing action with axially-slidable combining nozzle
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/44—Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42
- F04F5/46—Arrangements of nozzles
- F04F5/461—Adjustable nozzles
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention provides an oil return ejector and an aircraft engine fuel system comprising the same, wherein the oil return ejector comprises a nozzle shell and a throat pipe assembly which are butted and communicated; the nozzle is arranged in the nozzle shell, and the outer end face of the nozzle is abutted against the outer end part of the nozzle shell, so that the nozzle can slide left and right in the nozzle shell; the through hole is formed in the position, close to the outer end face of the nozzle, of the nozzle shell, when oil returned by the high-pressure pump returns from the nozzle, the hydraulic pressure of the returned oil pushes the nozzle to slide into the nozzle shell, the through hole is communicated with the interior of the nozzle shell, and the returned oil bypasses the through hole and flows out of the nozzle shell. The aircraft engine fuel system comprises the oil return ejector. The invention has the following advantages: firstly, the functions of the distribution jet nozzle are integrated, so that the weight is reduced; secondly, the spring characteristic and the shape of the hole are matched, and the distribution characteristic is optimized; thirdly, the throat nozzle distance is adjustable, and the jet flow efficiency is optimized; fourthly, the mechanism is simple and reliable, can be adjusted spontaneously, and has long service life.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to an oil return ejector and an aircraft engine fuel system comprising the same.
Background
FIG. 1 is a schematic diagram of a conventional aircraft engine fuel system. As shown in fig. 1, a conventional aircraft engine fuel system 10 is mainly composed of a low pressure pump 11, a high pressure pump 12, a metering valve 13, a high pressure shutoff valve 14, an oil return valve 15, a differential pressure valve 16, a fuel manifold 17, a fuel nozzle 18, and the like. When the aircraft oil is pressurized by the low pressure pump 11 and the high pressure pump 12, the aircraft oil enters a fuel manifold 17 and a fuel nozzle 18 through a metering valve 13 and a high pressure shutoff valve 14 to be supplied to a combustion chamber of the engine. The metering valve 13 is used to meter the amount of fuel to the engine combustion chamber. The high pressure shut off valve 14 is used to maintain a sufficient minimum servo pressure for the system and to shut off fuel to the engine combustion chamber after engine shut down. The differential pressure shutter 16 is used to ensure a constant differential pressure across the metering shutter 13. This control of the position of the metering valve 13 controls the amount of fuel to the combustion chamber and the return valve 15 serves to return excess engine demand fuel provided by the high pressure pump 12 to the rear of the low pressure pump 11.
Because the high-pressure pump mostly adopts a constant-displacement pump, and the rotating shaft of the high-pressure pump and the N2 rotor are in gear transmission, the result is that when the engine speed is high but the required fuel flow is low, a large amount of high-pressure fuel can return to the low-pressure pump through the oil return valve, so that a series of problems of hydraulic power consumption, fuel system temperature rise and the like are caused.
One of the schemes is to increase a jet pump behind an oil return valve to improve the utilization rate of hydraulic power. FIG. 2 is a schematic diagram of a conventional aircraft engine fuel system with the addition of a jet pump. As shown in fig. 2, the fuel flow return position in this system is before the nozzle of the jet pump 19, but the aircraft engine fuel demand maximum differs greatly from the aircraft engine fuel demand minimum. At high rpm low flow points and some over-run cut points, the return valve 15 needs to return almost all of the fuel from the fuel pump to the front of the gear pump. Under the condition, the pressure of the fuel system can be increased to a high state in a short time, the unloading of the fuel pump is not facilitated, the service life of the fuel pump is influenced, the range of return oil flow is wide, and the matching design of the jet pump and the fuel system is difficult.
In view of this, in order to solve the problem of matching the jet pump with the whole fuel system and prevent the pressure in front of the jet pump nozzle in the large oil return state from being too high, a person skilled in the art needs to develop a novel oil return ejector structure urgently.
Disclosure of Invention
The invention provides an oil return ejector and an aircraft engine fuel system comprising the same, aiming at overcoming the technical problems of matching a jet pump with a fuel system and the defect that the pressure in front of a jet pump nozzle in a large oil return state is not too high in the prior art.
The invention solves the technical problems through the following technical scheme:
An oil return ejector is characterized by comprising
a nozzle housing and a throat assembly, the nozzle housing and the throat assembly interfacing and communicating;
the nozzle is installed in the nozzle shell, and the outer end face of the nozzle is abutted against the outer end part of the nozzle shell, so that the nozzle can slide left and right in the nozzle shell;
The nozzle shell is provided with a through hole close to the outer end face of the nozzle, when the high-pressure pump returns oil from the nozzle, the hydraulic pressure of the returned oil pushes the nozzle to slide in the nozzle shell, the through hole is communicated with the inside of the nozzle shell, and the returned oil flows out of the nozzle shell through the bypass of the through hole.
According to one embodiment of the invention, the nozzle comprises an inlet straight section, a main body straight section and an outlet tapered section which are sequentially connected into a whole, wherein the outer end surface of the inlet straight section is abutted against the outer end part of the nozzle shell, and a step surface is formed at the joint of the inlet straight section and the main body straight section;
A stop part is arranged on the inner wall surface of the nozzle shell, and an elastic part is arranged on the main body straight section of the nozzle;
When the nozzle is in the nozzle shell slides to the right, the step surface is used for abutting against one end part of the elastic component, and the abutting part is used for abutting against the other end part of the elastic component.
according to one embodiment of the invention, the resilient member is a spring.
According to an embodiment of the present invention, the stopper member is a boss portion that protrudes along an inner wall surface of the nozzle housing.
According to an embodiment of the present invention, the stopper member is a spring washer or a spring seat provided on an inner wall surface of the nozzle housing.
According to one embodiment of the invention, the abutment member is provided with an orifice.
according to one embodiment of the invention, the lower portion of the nozzle housing is provided with a drainage aperture located between the throat assembly and the abutment member.
According to one embodiment of the invention, the outer end of the nozzle housing is provided with a hollow cover plate comprising a base plate and a projection body provided on the base plate, the projection body being inserted into the outer end of the nozzle housing against the outer end of the nozzle.
According to one embodiment of the invention, the throat assembly includes a throat housing and a throat, the throat being mounted within the throat housing, the throat housing interfacing with the nozzle housing proximate the exit tapered section of the nozzle.
The invention also discloses an aircraft engine fuel system which is characterized by comprising the oil return ejector.
The positive progress effects of the invention are as follows: the oil return ejector and the aircraft engine fuel system comprising the same have the following advantages:
Firstly, the functions of the distribution jet nozzle are integrated, so that the weight is reduced;
Secondly, the spring characteristic and the shape of the hole are matched, and the distribution characteristic is optimized;
Thirdly, the throat nozzle distance is adjustable, and the jet flow efficiency is optimized;
Fourthly, the mechanism is simple and reliable, can be adjusted spontaneously, and has long service life.
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 like reference numerals denote like features throughout the several views, wherein:
FIG. 1 is a schematic diagram of a conventional aircraft engine fuel system.
FIG. 2 is a schematic diagram of a conventional aircraft engine fuel system with the addition of a jet pump.
FIG. 3 is a schematic diagram of an aircraft engine fuel system according to the present invention.
fig. 4 is a schematic structural diagram of the oil return ejector of the invention.
Fig. 5 is a state schematic diagram of the oil return ejector in a small oil return state.
Fig. 6 is a state schematic diagram of the oil return ejector in a medium oil return state.
Fig. 7 is a state schematic diagram of the oil return ejector in a large oil return state such as emergency stop.
[ reference numerals ]
Conventional aircraft engine fuel system 10
Low pressure pump 11, 21
high pressure pumps 12, 22
Metering flap 13, 23
High-pressure shut-off valves 14, 24
Oil return valves 15, 25
Differential pressure valves 16, 26
Fuel rail 17, 28
Fuel injection nozzle 18, 27
Jet pump 19
Aircraft engine fuel system 20
Oil return ejector 100
Nozzle housing 110
Nozzle 120
Through-hole 111
Inlet straight section 121
Main body straight section 122
Outlet tapered section 123
step surface 124
Spring 125
Rest part 112
Throttle hole 113
Drainage apertures 114
Cover plate 115
Bottom plate 116
convex body 117
Throat housing 130
Throat pipe 131
Induced flow A
Is induced to flow B
Nozzle fuel C
Bypass fuel D
Detailed Description
in order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts.
Further, although the terms used in the present invention are selected from publicly known and used terms, some of the terms mentioned in the description of the present invention may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein.
Furthermore, it is required that the present invention is understood, not simply by the actual terms used but by the meaning of each term lying within.
FIG. 3 is a schematic diagram of an aircraft engine fuel system according to the present invention. As shown in fig. 3, the aircraft engine fuel system 20 mainly includes a low-pressure pump 21, a high-pressure pump 22, a metering valve 23, a high-pressure shutoff valve 24, an oil return valve 25, a differential pressure valve 26, a fuel nozzle 27, a fuel manifold 28, and an oil return ejector 100 with a bypass function. Specifically, the high-pressure pump 22, the metering shutter 23, and the high-pressure shutoff shutter 24 are connected in this order, and the high-pressure shutoff shutter 24 is connected to the fuel injection nozzle 27 through the fuel manifold 28. The passage between the high-pressure pump 22 and the metering shutter 23 communicates with the oil return shutter 25, the passage between the metering shutter 23 and the oil return shutter 25 communicates with the differential pressure shutter 26, and the passage between the metering shutter 23 and the high-pressure shutoff shutter 24 communicates with the differential pressure shutter 26. Meanwhile, the differential pressure valve 26, the oil return valve 25 and the oil return ejector 100 are connected in sequence. The inlet and the outlet of the oil return ejector 100 here are connected to the high-pressure pump 22, respectively, and the bypass of the oil return ejector 100 is connected to the low-pressure pump 21.
According to the above description, the aircraft engine fuel system according to the present invention adds a bypass to the return oil ejector 100, so that the return oil can pass through the nozzle of the return oil ejector 100 or directly enter the exit port of the return oil ejector 29 by selecting the pressure. When the oil return amount is increased suddenly to cause the oil return pressure to be increased sharply, the bypass valve can be opened to release the pressure of the oil pump. Meanwhile, in the principle, the nozzle value of the oil return ejector 100 can be selected to be smaller in diameter, and the pressure of the outlet of the oil return ejector 100 is increased. Therefore, the risk of measurement function failure caused by poor oil return due to the small nozzle value in the scheme of figure 2 in the prior art can be solved.
Fig. 4 is a schematic structural diagram of the oil return ejector of the invention. As shown in fig. 4, further specifically, the disclosed oil return ejector 100 includes a nozzle housing 110, a nozzle 120, and a throat assembly, the nozzle housing 110 and the throat assembly interfacing and communicating. The nozzle 120 is installed in the nozzle housing 110 with an outer end surface of the nozzle 120 abutting against an outer end portion of the nozzle housing 110 so that the nozzle 120 can slide left and right in the nozzle housing 110. Meanwhile, a through hole 111 is formed in the nozzle housing 110 near the outer end surface of the nozzle 120, when the high-pressure pump 22 returns oil from the nozzle 120, the hydraulic pressure of the returned oil pushes the nozzle 120 to slide into the nozzle housing 110, the through hole 111 communicates with the inside of the nozzle housing 110, and the returned oil bypasses the through hole 111 and flows out of the nozzle housing 110.
Preferably, the nozzle 120 includes an inlet straight section 121, a main body straight section 122 and an outlet tapered section 123 which are connected in sequence as a whole, an outer end surface of the inlet straight section 121 abuts against an outer end portion of the nozzle housing 110, and a step surface 124 is formed at a connection position of the inlet straight section 121 and the main body straight section 122. A stopper 112 is provided on an inner wall surface of the nozzle housing 110, and an elastic member, preferably a spring 125, is mounted on the main body straight section 122 of the nozzle 120. When the nozzle 120 is slid rightward in the nozzle housing 110, the stepped surface 124 is used to abut against one end portion of the elastic member, and the abutting member 112 is used to abut against the other end portion of the elastic member.
Further, the stopper member 112 may be provided as a convex portion that protrudes along the inner wall surface of the nozzle housing 110. Alternatively, the stopper 112 may be a spring ring or a spring seat (not shown) provided on the inner wall surface of the nozzle housing 110. These structures may function to stop against the resilient member.
Further, the stopper member 112 is provided with an orifice 113. The lower portion of the nozzle housing 110 is provided with a drainage aperture 114 and the drainage aperture 114 is located between the throat assembly and the abutment member 112. The throat assembly herein includes a throat housing 130 and a throat 131, the throat 131 being mounted within the throat housing 130, the throat housing 130 interfacing with the nozzle housing 110 proximate the exit tapered section 123 of the nozzle 120.
preferably, the outer end of the nozzle housing 110 is provided with a hollow cover plate 115, the cover plate 115 includes a base plate 116 and a protrusion body 117, the protrusion body 117 is disposed on the base plate 116, and the protrusion body 117 is inserted into the outer end of the nozzle housing 110, against the outer end of the nozzle 120.
As described above, the nozzle housing 110 allows the nozzle 120 to slide left and right within the housing, resting left against the cover plate 115, and resting right against the stop member 112. Spring 125 acts on the right shoulder of nozzle 120, applying a force to the left against nozzle 120.
Fig. 5 is a state schematic diagram of the oil return ejector in a small oil return state.
As shown in fig. 5, the sum of the flow rates of the injection flow a and the injected flow B is equal to the displacement of the high-pressure pump, and the flow rate of the injected flow B is equal to the flow rate passing through the combustion chamber. Because the high-pressure return oil flow is small, the pressure is not enough to enable the nozzle 120 to overcome the elastic force of the shielding section, the return oil is not bypassed, and the return oil completely enters the nozzle 120 to serve as nozzle fuel oil C.
fig. 6 is a state schematic diagram of the oil return ejector in a medium oil return state.
As shown in fig. 6, when the engine is operating in a high-speed low-flow state, the nozzle 120 moves to a certain middle position under the action of the return oil pressure and the spring force, and the return oil (i.e., the injection flow a) pressing force is distributed into the nozzle fuel C and the bypass fuel D, so that the outlet pressure of the return oil ejector reaches the maximum.
That is, because the high-pressure return oil flow is large, the pressure in front of the nozzle is high, the preset elastic force of the spring is overcome, and the nozzle fuel oil and the bypass fuel oil are finally stopped at the force balance position to be distributed, so that the outlet pressure of the jet pump is the highest.
Fig. 7 is a state schematic diagram of the oil return ejector in a large oil return state such as emergency stop.
As shown in fig. 7, when an emergency stop occurs, a large amount of high-pressure pump return oil (i.e., the injection flow a) returns from the nozzle 120, and the nozzle 120 receives a hydraulic force rightward and slides to a right rest position against a spring force. The left shoulder of the nozzle 120 is subjected to smooth and sharp edge treatment, and forms a bypass oil outlet with the through hole 111 on the nozzle shell 110, so that fuel oil is bypassed, the return oil pressure is reduced, and the fuel pump is unloaded.
That is to say, because the high-pressure return oil flow is extremely high, the pressure in front of the nozzle is extremely high, the elasticity of all the springs is overcome, the nozzle is stopped at the right side, most return oil is returned to the inlet of the high-pressure pump through the bypass through hole, and the high-pressure pump is unloaded.
As mentioned above, the oil return ejector and the aircraft engine fuel system comprising the same can improve the system matching performance and relieve the pressure of the engine fuel system in emergency stop and other states.
The nozzle of the oil return ejector is designed with variable pressure, the straight inlet section of the nozzle and the inner wall (lining) of the shell form a valve core lining component, the right shoulder of the nozzle and the shell form a control cavity, and the function of the nozzle is increased by the original function of increasing the fuel oil exit speed and increasing the function of bypass distribution. Meanwhile, the spring characteristic and the shape of the hole have distribution performance matched with a system, a damping hole is arranged between the spring cavity and the return oil to control the dynamic characteristic of the nozzle, the throat nozzle distance can also change when the nozzle moves left and right, and the efficiency of the jet pump can be optimized according to the system characteristic. The problem of matching the oil return ejector with the whole fuel system is solved, and the front pressure of a nozzle of the oil return ejector is not too high in a large oil return state.
In summary, the oil return ejector and the aircraft engine fuel system comprising the same have the following advantages:
Firstly, the functions of the distribution jet nozzle are integrated, so that the weight is reduced;
Secondly, the spring characteristic and the shape of the hole are matched, and the distribution characteristic is optimized;
thirdly, the throat nozzle distance is adjustable, and the jet flow efficiency is optimized;
Fourthly, the mechanism is simple and reliable, can be adjusted spontaneously, and has long service life.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (10)
1. An oil return ejector is characterized by comprising
A nozzle housing and a throat assembly, the nozzle housing and the throat assembly interfacing and communicating;
The nozzle is installed in the nozzle shell, and the outer end face of the nozzle is abutted against the outer end part of the nozzle shell, so that the nozzle can slide left and right in the nozzle shell;
The nozzle shell is provided with a through hole close to the outer end face of the nozzle, when the high-pressure pump returns oil from the nozzle, the hydraulic pressure of the returned oil pushes the nozzle to slide in the nozzle shell, the through hole is communicated with the inside of the nozzle shell, and the returned oil flows out of the nozzle shell through the bypass of the through hole.
2. the oil return ejector according to claim 1, wherein the nozzle comprises an inlet straight section, a main body straight section and an outlet tapered section which are sequentially connected into a whole, the outer end face of the inlet straight section is abutted against the outer end part of the nozzle shell, and a step face is formed at the joint of the inlet straight section and the main body straight section;
a stop part is arranged on the inner wall surface of the nozzle shell, and an elastic part is arranged on the main body straight section of the nozzle;
when the nozzle is in the nozzle shell slides to the right, the step surface is used for abutting against one end part of the elastic component, and the abutting part is used for abutting against the other end part of the elastic component.
3. The oil return ejector of claim 2 wherein the resilient member is a spring.
4. The oil return ejector according to claim 2, wherein the stopper member is a boss protruding along an inner wall surface of the nozzle housing.
5. The oil return ejector according to claim 3, wherein the stopper member is a spring union or a spring seat provided on an inner wall surface of the nozzle housing.
6. The oil return eductor of claim 2 wherein the stop member is provided with an orifice.
7. The oil return eductor of claim 2 wherein the lower portion of the nozzle housing is provided with a drainage aperture located between the throat assembly and the stop member.
8. the oil return ejector according to claim 2, wherein the outer end of the nozzle housing is provided with a hollow cover plate, the cover plate including a bottom plate and a protrusion body provided on the bottom plate, the protrusion body being inserted into the outer end of the nozzle housing against the outer end of the nozzle.
9. The oil return eductor of claim 2 wherein the throat assembly comprises a throat housing and a throat, the throat being mounted within the throat housing, the throat housing interfacing with the nozzle housing proximate the exit taper of the nozzle.
10. An aircraft engine fuel system, characterized in that it comprises an oil return ejector according to any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810530735.3A CN110541849B (en) | 2018-05-29 | 2018-05-29 | Oil return ejector and aircraft engine fuel system comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810530735.3A CN110541849B (en) | 2018-05-29 | 2018-05-29 | Oil return ejector and aircraft engine fuel system comprising same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110541849A true CN110541849A (en) | 2019-12-06 |
| CN110541849B CN110541849B (en) | 2021-01-15 |
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ID=68700958
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810530735.3A Active CN110541849B (en) | 2018-05-29 | 2018-05-29 | Oil return ejector and aircraft engine fuel system comprising same |
Country Status (1)
| Country | Link |
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| CN (1) | CN110541849B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111120034A (en) * | 2019-12-20 | 2020-05-08 | 中国北方发动机研究所(天津) | Injection type engine oil circulation oil return device |
| CN112392605A (en) * | 2020-10-30 | 2021-02-23 | 中国航发西安动力控制科技有限公司 | Differential pressure mechanism |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0324931A (en) * | 1989-06-22 | 1991-02-01 | Sekisui Chem Co Ltd | Nozzle apparatus for injection molding |
| CN1299952A (en) * | 1999-12-10 | 2001-06-20 | 珠海市声速科技有限公司 | Supersonic four-head by-pass reducing power-saving device |
| US20060269422A1 (en) * | 2005-05-31 | 2006-11-30 | Banyard Richard L | Vacuum generator for vacuum-decay leak testing the evaporative emissions system of a motor vehicle |
| CN103619629A (en) * | 2011-06-27 | 2014-03-05 | 考特克斯·特克斯罗恩有限公司及两合公司 | Device for pressure-dependent opening of a suction intake |
| CN105782494A (en) * | 2016-05-18 | 2016-07-20 | 洪顺生 | Jet regulating valve |
| CN207451748U (en) * | 2017-08-15 | 2018-06-05 | 唐山骏驰水务工程有限公司 | A kind of jet aerator |
| CN108131335A (en) * | 2016-11-30 | 2018-06-08 | 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
- 2018-05-29 CN CN201810530735.3A patent/CN110541849B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0324931A (en) * | 1989-06-22 | 1991-02-01 | Sekisui Chem Co Ltd | Nozzle apparatus for injection molding |
| CN1299952A (en) * | 1999-12-10 | 2001-06-20 | 珠海市声速科技有限公司 | Supersonic four-head by-pass reducing power-saving device |
| US20060269422A1 (en) * | 2005-05-31 | 2006-11-30 | Banyard Richard L | Vacuum generator for vacuum-decay leak testing the evaporative emissions system of a motor vehicle |
| CN103619629A (en) * | 2011-06-27 | 2014-03-05 | 考特克斯·特克斯罗恩有限公司及两合公司 | Device for pressure-dependent opening of a suction intake |
| CN105782494A (en) * | 2016-05-18 | 2016-07-20 | 洪顺生 | Jet regulating valve |
| CN108131335A (en) * | 2016-11-30 | 2018-06-08 | 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 |
| CN207451748U (en) * | 2017-08-15 | 2018-06-05 | 唐山骏驰水务工程有限公司 | A kind of jet aerator |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111120034A (en) * | 2019-12-20 | 2020-05-08 | 中国北方发动机研究所(天津) | Injection type engine oil circulation oil return device |
| CN112392605A (en) * | 2020-10-30 | 2021-02-23 | 中国航发西安动力控制科技有限公司 | Differential pressure mechanism |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110541849B (en) | 2021-01-15 |
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