CN111271190A - Ram air turbine miniflow temperature control circulation structure - Google Patents
Ram air turbine miniflow temperature control circulation structure Download PDFInfo
- Publication number
- CN111271190A CN111271190A CN201811476722.9A CN201811476722A CN111271190A CN 111271190 A CN111271190 A CN 111271190A CN 201811476722 A CN201811476722 A CN 201811476722A CN 111271190 A CN111271190 A CN 111271190A
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- Prior art keywords
- temperature
- air turbine
- ram air
- flow
- pressure
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
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- 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
- F02C7/224—Heating fuel before feeding to the burner
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- 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
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
Abstract
The invention relates to a micro-flow temperature control circulation structure of a ram air turbine, which is characterized in that: the device comprises a micro-flow pressure and temperature reduction and increase device (1), a temperature flow circulation oil way (2) and a temperature flow circulation control device (3), wherein the micro-flow pressure and temperature reduction and increase device (1) is connected with a high-pressure end of an airplane hydraulic system, small-flow oil is introduced into a ram air turbine (4) from the micro-flow pressure and temperature increase device, the oil is subjected to pressure and temperature reduction treatment, an oil way in the whole ram air turbine (4) and a hydraulic pump (5) are heated through the temperature flow circulation oil way (2), and the temperature flow circulation control device (3) is installed inside the hydraulic pump (5) and is respectively connected with the micro-flow pressure and temperature reduction and increase device (1) and the temperature flow circulation oil way. The method obviously improves the starting performance of the ram air turbine in the high-altitude low-temperature environment on the premise of not influencing the parameters of the ram air turbine (ram air turbine), such as weight, volume, efficiency and the like.
Description
Technical Field
The invention belongs to the field of functional design of emergency energy systems, and relates to a micro-flow temperature control circulation structure of a ram air turbine.
Background
The ram air turbine (ram air turbine) is an efficient airborne emergency energy device, is the last emergency device on the airplane, and when the airplane enters an emergency state in the air, the ram air turbine needs to be started quickly, so that the airplane can acquire emergency energy in the fastest time, and the airplane is guaranteed to be emergency and forced landing safety to the maximum extent.
The use envelope of the ram air turbine coincides with the aircraft flight envelope and the use requirements are met under all flight altitude conditions. When a product is in a high-altitude environment, because the ram air turbine cabin of an airplane is generally not a heat-insulating cabin, the environment temperature is lower than-55 ℃, the temperature of oil liquid in the ram air turbine hydraulic pump is also lower, and if the ram air turbine is put into use, the start time of the ram air turbine can be obviously delayed because the oil liquid in the ram air turbine hydraulic pump is in a low-temperature viscous state.
Disclosure of Invention
The purpose of the invention is as follows: the method is characterized in that high-pressure oil subjected to pressure reduction and temperature increase is circulated in the ram air turbine hydraulic pump, so that the internal oil temperature of the hydraulic pump in a high-altitude low-temperature environment is kept when the ram air turbine is in a non-working state, the ram air turbine can be quickly started, and after the ram air turbine normally works, an internal 'warm flow' circulating oil way is cut off, and the output efficiency of the ram air turbine is improved.
The technical scheme of the invention is as follows: the utility model provides a ram air turbine miniflow control by temperature change circulation structure, including miniflow step-down heating apparatus 1, warm current circulation oil circuit 2, warm current circulation control device 3, wherein, miniflow step-down heating apparatus 1 is connected with aircraft hydraulic system high-pressure end, from wherein introduce among the little fluid entering ram air turbine 4, fluid is through step-down heating processing, oil circuit and hydraulic pump 5 heating in whole ram air turbine 4 through warm current circulation oil circuit 2, warm current circulation control device 3 installs inside hydraulic pump 5, respectively with miniflow step-down heating apparatus 1, warm current circulation oil circuit 2 is established ties.
When the aircraft normally flies, the ram air turbine 4 is in a non-working state, high-pressure oil of an aircraft hydraulic system is subjected to pressure reduction and temperature increase, flows into the hydraulic pump 5, and finally returns to a low-pressure oil way of the aircraft hydraulic system through the warm flow circulating oil way 2;
when the airplane flies in emergency, the ram air turbine 4 enters a working state, and the warm flow circulating oil way 2 is cut off through the warm flow circulating control device 3, so that overlarge output internal leakage amount of the hydraulic pump 5 is prevented.
Preferably, the micro-flow pressure and temperature reducing and increasing device 1 is in the form of a one-way throttle valve and consists of a valve sleeve 6, a valve core A7, a plug 8, a return spring 9 and a retainer ring 10. Wherein, the valve core 7 is arranged inside the valve sleeve 6, the end surface of the valve core is in sealing fit with the valve sleeve 6, and the valve core 7 is provided with a throttling hole for reducing pressure and increasing temperature of the hydraulic oil. One end of a return spring 9 is limited and installed on the valve sleeve 6 through a retaining ring 10, and the other end of the return spring is contacted with the valve core A7 to provide return elastic force for the valve core A7. The plug 8 is mounted on the valve housing 6 by means of a collar 10.
Preferably, in a standby state of the ram air turbine 4, high-pressure oil introduced into the aircraft hydraulic system enters the warm flow circulating oil path 2 from a small hole in the center of the valve core of the micro-flow pressure and temperature reducing and increasing device 1, and then the oil path of the ram air turbine 4 and the hydraulic pump are heated; the ram air turbine 4 supplies oil to the aircraft hydraulic source in the air use state, and the oil way circulates reversely.
Preferably, the warm flow circulation control device 3 is in the form of a hydraulic piston, and consists of a mounting seat 11, a piston sleeve 12, a piston spring A13, a piston spring B14, a piston core 15 and a piston spring C16. One end of the piston spring C15 is limited by the mounting seat 11, and the other end is connected with the piston sleeve 12. The piston core 15 is mounted inside the piston sleeve 12, and is position-adjusted by a piston spring a13 and a piston spring B14.
Preferably, when the ram air turbine 4 is on standby in the air, the high-pressure oil port of the hydraulic pump 5 is communicated with the internal leakage port of the pump, the piston core 15 is in the open position, and hydraulic oil can circulate in the RAT hydraulic pump through the internal leakage port; when the ram air turbine 4 is used in the air, the piston core 15 is in the closed position, and the high-pressure oil output by the hydraulic pump does not cause efficiency reduction due to leakage in the hydraulic pump.
The invention has the advantages that:
the invention provides a micro-flow temperature control circulation structure of a ram air turbine. The method is characterized in that high-pressure oil subjected to pressure reduction and temperature increase is circulated in the ram air turbine hydraulic pump, so that the internal oil temperature of the hydraulic pump in a high-altitude low-temperature environment is kept when the ram air turbine is in a non-working state, the ram air turbine can be quickly started, and after the ram air turbine normally works, an internal 'warm flow' circulating oil way is cut off, and the output efficiency of the ram air turbine is improved. The method can obviously improve the starting performance of the ram air turbine in the high-altitude low-temperature environment on the premise of not influencing the parameters of the ram air turbine (ram air turbine), such as weight, volume, efficiency and the like, and has better application prospect and economical efficiency.
Description of the drawings:
FIG. 1 is a schematic view of the overall structure;
FIG. 2 is a schematic view of a micro-flow pressure and temperature reducing device;
FIG. 3 is a schematic view of the structure of the warm flow circulation control device;
Detailed Description
The invention is described in detail below with reference to the accompanying drawings. Please refer to fig. 1-3 of the specification.
1. A pressure and temperature reduction and increase device (1) is arranged between a ram air turbine (ram air turbine) (4) and a high-pressure oil way of an airplane hydraulic system; a warm flow circulating oil way (2) is designed inside a hydraulic pump of a ram air turbine (ram air turbine) (4); a warm flow circulation control device (3) is designed in a hydraulic pump of a ram air turbine (ram air turbine) (4). The structure diagram is shown in figure 1.
2. The microflow pressure reducing and temperature increasing device is in a one-way throttle valve form and comprises a valve core, a valve sleeve, a plug, a return spring, a check ring and other parts. The structure diagram is shown in figure 2.
3. When the ram air turbine is used in the air, the high-pressure oil output by the ram air turbine reversely opens the valve core to provide emergency hydraulic energy for the airplane.
4. The internal warm flow circulation control device of the ram air turbine hydraulic pump is in the form of a hydraulic piston. The structure diagram is shown in figure 3.
When the ram air turbine is in standby in the air, the valve core is located at the open position of the warm flow oil path, the high-pressure oil port of the ram air turbine hydraulic pump is communicated with the internal leakage port of the pump, circulation can be achieved through the internal leakage port in the ram air turbine hydraulic pump through warm flow, when the ram air turbine is used in the air, the valve core is located at the closed position of the warm flow oil path, the high-pressure oil port of the ram air turbine hydraulic pump is disconnected with the internal leakage port of the pump, and at the moment, high-pressure oil output by the ram air turbine hydraulic pump cannot cause efficiency reduction due to internal leakage of the hydraulic pump.
Claims (6)
1. The utility model provides a ram air turbine miniflow control by temperature change circulation structure which characterized in that: the device comprises a micro-flow pressure and temperature reduction and increase device (1), a temperature flow circulation oil way (2) and a temperature flow circulation control device (3), wherein the micro-flow pressure and temperature reduction and increase device (1) is connected with a high-pressure end of an airplane hydraulic system, small-flow oil is introduced into a ram air turbine (4) from the micro-flow pressure and temperature increase device, the oil is subjected to pressure and temperature reduction treatment, an oil way in the whole ram air turbine (4) and a hydraulic pump (5) are heated through the temperature flow circulation oil way (2), and the temperature flow circulation control device (3) is installed inside the hydraulic pump (5) and is respectively connected with the micro-flow pressure and temperature reduction and increase device (1) and the temperature flow circulation oil way.
2. The ram air turbine micro-fluidic temperature-controlled circulation structure of claim 1, wherein:
when the aircraft normally flies, the ram air turbine (4) is in a non-working state, high-pressure oil of an aircraft hydraulic system is subjected to pressure reduction and temperature increase, flows into the hydraulic pump (5), and finally returns to a low-pressure oil way of the aircraft hydraulic system through the warm flow circulating oil way (2); when the airplane flies in an emergency, the ram air turbine (4) enters a working state, and the warm flow circulating oil way (2) is cut off through the warm flow circulating control device (3) to prevent overlarge output internal leakage amount of the hydraulic pump (5).
3. The ram air turbine micro-fluidic temperature-controlled circulation structure of claim 1, wherein: the microflow pressure and temperature reducing and increasing device (1) is in a one-way throttle valve form and consists of a valve sleeve (6), a valve core A (7), a plug (8), a return spring (9) and a retainer ring (10); the valve core (7) is arranged in the valve sleeve (6), the end face of the valve core is in sealing fit with the valve sleeve (6), and throttling holes are designed on the valve core (7) and used for reducing pressure and increasing temperature of hydraulic oil; one end of a return spring (9) is limited and installed on the valve sleeve (6) through a retaining ring (10), and the other end of the return spring is contacted with the valve core A (7) to provide return elasticity for the valve core A (7); the choke plug (8) is arranged on the valve sleeve (6) through a retaining ring (10).
4. The ram air turbine micro-flow temperature control circulation structure as claimed in claim 3, wherein in a standby state of the ram air turbine (4), high-pressure oil introduced into an aircraft hydraulic system enters the warm flow circulation oil path (2) from a small hole in the center of a valve core of the micro-flow pressure and temperature reduction and increase device (1), so as to heat the oil path of the ram air turbine (4) and a hydraulic pump; the ram air turbine (4) supplies oil to the aircraft hydraulic source in the air use state, and the oil way reversely circulates.
5. The ram air turbine micro-flow temperature control circulation structure as claimed in claim 1, wherein the warm flow circulation control device (3) is in the form of a hydraulic piston, and is composed of a mounting seat (11), a piston sleeve (12), a piston spring A (13), a piston spring B (14), a piston core (15) and a piston spring C (16); one end of a piston spring C (15) is limited by a mounting seat (11), and the other end of the piston spring C is connected with a piston sleeve (12); the piston core (15) is installed in the piston sleeve (12), and position adjustment is performed through a piston spring A (13) and a piston spring B (14).
6. The ram air turbine micro-flow temperature control circulation structure according to claim 5, wherein when the ram air turbine (4) is on standby in the air, the high pressure port of the hydraulic pump (5) is connected to the internal leakage port of the pump, the piston core (15) is in the open position, and hydraulic oil can circulate inside the RAT hydraulic pump through the internal leakage port; when the ram air turbine (4) is used in the air, the piston core (15) is in a closed position, and high-pressure oil output by the hydraulic pump cannot cause efficiency reduction due to leakage in the hydraulic pump.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811476722.9A CN111271190B (en) | 2018-12-04 | 2018-12-04 | Ram air turbine miniflow temperature control circulation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811476722.9A CN111271190B (en) | 2018-12-04 | 2018-12-04 | Ram air turbine miniflow temperature control circulation structure |
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| Publication Number | Publication Date |
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| CN111271190A true CN111271190A (en) | 2020-06-12 |
| CN111271190B CN111271190B (en) | 2022-11-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811476722.9A Active CN111271190B (en) | 2018-12-04 | 2018-12-04 | Ram air turbine miniflow temperature control circulation structure |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB751850A (en) * | 1953-02-16 | 1956-07-04 | Bristol Aeroplane Co Ltd | Improvements in or relating to fuel supply systems for ram-jet engines |
| US20070160460A1 (en) * | 2006-01-12 | 2007-07-12 | Honeywell International, Inc. | Ram air turbine with compound geartrain gearbox |
| CN201109490Y (en) * | 2007-06-19 | 2008-09-03 | 中国航空工业第一集团公司沈阳飞机设计研究所 | Aeroplane hydraulic oil rapid heating-up device |
| CN101825126A (en) * | 2010-03-27 | 2010-09-08 | 新乡平原航空技术工程有限公司 | Portable field detection device of helicopter hydraulic system |
| CN103016206A (en) * | 2011-09-21 | 2013-04-03 | 通用电气公司 | Ram air turbine with integrated heat exchanger |
| CN104632741A (en) * | 2014-12-10 | 2015-05-20 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Warm flow valve for hydraulic type ram air turbine |
| CN204664026U (en) * | 2015-04-23 | 2015-09-23 | 南京王行航空附件维修工程有限公司 | A kind of plane spoiler servocontroller testing apparatus |
-
2018
- 2018-12-04 CN CN201811476722.9A patent/CN111271190B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB751850A (en) * | 1953-02-16 | 1956-07-04 | Bristol Aeroplane Co Ltd | Improvements in or relating to fuel supply systems for ram-jet engines |
| US20070160460A1 (en) * | 2006-01-12 | 2007-07-12 | Honeywell International, Inc. | Ram air turbine with compound geartrain gearbox |
| CN201109490Y (en) * | 2007-06-19 | 2008-09-03 | 中国航空工业第一集团公司沈阳飞机设计研究所 | Aeroplane hydraulic oil rapid heating-up device |
| CN101825126A (en) * | 2010-03-27 | 2010-09-08 | 新乡平原航空技术工程有限公司 | Portable field detection device of helicopter hydraulic system |
| CN103016206A (en) * | 2011-09-21 | 2013-04-03 | 通用电气公司 | Ram air turbine with integrated heat exchanger |
| CN104632741A (en) * | 2014-12-10 | 2015-05-20 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Warm flow valve for hydraulic type ram air turbine |
| CN204664026U (en) * | 2015-04-23 | 2015-09-23 | 南京王行航空附件维修工程有限公司 | A kind of plane spoiler servocontroller testing apparatus |
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| Publication number | Publication date |
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| CN111271190B (en) | 2022-11-08 |
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