CN113606042A - Mounting structure of automatically-locked starting valve device on aircraft engine - Google Patents
Mounting structure of automatically-locked starting valve device on aircraft engine Download PDFInfo
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- CN113606042A CN113606042A CN202110943037.8A CN202110943037A CN113606042A CN 113606042 A CN113606042 A CN 113606042A CN 202110943037 A CN202110943037 A CN 202110943037A CN 113606042 A CN113606042 A CN 113606042A
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 14
- 238000009434 installation Methods 0.000 claims abstract description 3
- 238000007789 sealing Methods 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000000740 bleeding effect Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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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
- 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
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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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
- F02C7/26—Starting; Ignition
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluid-Driven Valves (AREA)
Abstract
The invention discloses an installation structure of an automatic locking starting valve device on an aircraft engine, which comprises: the mounting seat E is mounted outside a casing gas collecting cavity C of the high-pressure compressor; the starting valve device is arranged on the mounting seat E, and when the valve is in an open state and deflates, the valve is far away from the inside of the gas collecting cavity C; the mounting seat F of the combustion chamber casing is communicated with an air inlet at the upper part of the starting valve device; the air in the combustion chamber entering the air inlet at the upper part of the starting valve device through the mounting seat F and the air pressure in the high-pressure compressor gas collecting cavity C entering the lower part of the starting valve device through the mounting seat E form a pressure difference, when the pressure difference is not enough to overcome the spring elasticity of the starting valve device, the starting valve device is in an open state, at the moment, the valve of the starting valve device is in a state of being far away from the gas collecting cavity C, and the problem that the valve in the prior art can block the airflow of the gas collecting cavity is solved.
Description
Technical Field
The invention relates to an installation structure of an automatic locking starting valve device on an aircraft engine, and belongs to the technical field of aircraft engines.
Background
When the aircraft engine is started, the flow capacity of the front stage and the rear stage of the high-pressure compressor is not matched, the flow capacity of the rear stage is weaker than that of the front stage, so that blockage is easily formed at the rear stage, and further the axial velocity is suddenly reduced to cause surge at the front stage; the aircraft engine is the heart of an airplane, and the surge problem of the engine always restricts the development of a turbine engine, influences the performance of the engine and even causes serious damage to the engine; in order to ensure that the turbine engine does not surge under all working conditions, commonly adopted anti-surge measures comprise a double-rotor or three-rotor structure, intermediate stage air discharge of a gas compressor, adjustable inlet guide vanes, adjustable flow vanes and the like;
the surge margin of the compressor is improved when the engine is started, a method of intermediate stage air bleeding of the compressor is generally adopted, an air bleeding system is arranged in the intermediate stage of the compressor, the compressor is opened when the engine is started, the blocking condition of the rear stage is relieved due to the intermediate stage air bleeding, meanwhile, the axial speed of the front stage is increased due to the reduction of the resistance of an air flow path, so that the surge condition of the front stage is improved, and the air bleeding system is formed by an air pressure control air bleeding valve arranged on the compressor;
in the air pressure control air release valve disclosed in the Chinese patent publication No. CN204783279U, an air compressor system with the air pressure control air release valve and an airplane, when the air pressure control air release valve is arranged on an air compressor to form a structure, when an engine is started or enters a slow-speed vehicle state, the valve needs to be separated downwards from the bottom of a shell to be in an open air release state, the valve at the moment moves downwards to extend into an outward exhaust port of an air collection cavity of a casing of the high-pressure air compressor, the problem that the valve can block airflow flowing in the air collection cavity exists, the improvement effect of front-stage surging is limited, and surging still occurs when airflow flowing quantity is large.
Disclosure of Invention
In order to solve the technical problem, the invention provides a mounting structure of an automatic locking starting valve device on an aircraft engine.
The invention is realized by the following technical scheme.
The invention provides a mounting structure of an automatic locking starting valve device on an aircraft engine, which comprises:
the mounting seat E is mounted outside a casing gas collecting cavity C of the high-pressure compressor;
the starting valve device is arranged on the mounting seat E, and when the valve is in an open state and deflates, the valve is far away from the inside of the gas collecting cavity C;
and the mounting seat F of the combustion chamber casing is communicated with an air inlet at the upper part of the starting valve device.
When the starting or slow-speed vehicle is started, air in the combustion chamber entering an air inlet at the upper part of the starting valve device through the mounting seat F and air pressure in the high-pressure compressor air collecting cavity C entering the lower part of the starting valve device through the mounting seat E form pressure difference, when the pressure difference is not enough to overcome the spring elasticity of the starting valve device, the starting valve device is in an open state, and at the moment, the valve of the starting valve device is in a state of being far away from the air collecting cavity C, so that the problem that the valve in the prior art can block airflow flowing of the air collecting cavity is solved, the front-stage surge effect is improved, and the surge phenomenon cannot occur when the airflow flowing quantity is large.
The starting shutter device includes:
the middle part of the bottom surface of the outer sleeve is provided with an air inlet communicated with the air collecting cavity C;
the cone and the shell are fixedly arranged in sequence along the circumferential direction of the outer sleeve, and the cone is positioned between the outer sleeve and the shell; the upper part of the cone and the shell form a cavity, the lower part of the cone and the outer sleeve form a cavity, vent holes which are correspondingly communicated are arranged on the cone and the shell which are close to the joint of the cone and the outer sleeve, and gas can flow from the gas collection cavity C to the vent holes and is discharged out of the outer duct;
the small end of the piston rod can slidably penetrate through the middle of the cone and is fixedly provided with a valve, the piston rod slides downwards to drive the valve to be in conical surface tight contact with the air inlet of the outer sleeve, the air passage is closed, the piston rod slides upwards to drive the valve to be separated from the air inlet of the outer sleeve, and the air passage is opened;
the large end of the piston rod is in slidable close contact with the inner wall of a cavity formed by the cone and the shell, and the cavity formed by the cone and the shell is divided into an upper cavity A and a lower cavity B by the large end of the piston rod;
a through hole for gas to enter and exit is arranged on the cone at the part shielded by the valve, so that the cavity B is communicated with the gas collection cavity C;
the outside of the small end of the piston rod is sleeved with a spring of which the upper end and the lower end are respectively contacted with the large end of the piston rod and the cone, the spring is always positioned in the cavity B when elastically deformed, and the pressure difference between the cavity A and the cavity B drives the piston rod to overcome the elasticity of the spring to slide up and down;
the upper part of the shell is provided with a horizontal air inlet which is communicated with the cavity A.
The cone and the shell are fixedly mounted with the outer sleeve in sequence through pin positioning and screws.
The piston rod is T-shaped.
The periphery of the large end of the piston rod is provided with a sealing ring which is in slidable close contact with the inner wall of a cavity formed by the cone and the shell.
And a valve is fixedly screwed at the small end of the piston rod penetrating through the middle part of the cone through a nut E.
The mounting seat E is fixedly connected with the bottom surface of the outer sleeve, and the gas collecting cavity C is correspondingly communicated with the lower gas inlet of the outer sleeve of the starting valve device, so that the gas collecting cavity C is communicated with the lower gas inlet of the starting valve device; the gas in the gas collection cavity C can enter the cavity B from the cavity formed by the lower part of the cone and the outer sleeve, so that the pressure of the cavity B is the same as the air pressure of the gas collection cavity C of the high-pressure compressor casing; or the gas in the gas collecting cavity C can be discharged out of the bypass from the vent holes on the cone and the shell close to the joint of the outer sleeve.
The mounting seat E is fixedly connected with the bottom surface of the outer sleeve through a nut F and a stud.
The mounting seat F is communicated with the air inlet of the shell in a horizontal shape through a short pipe.
The mounting seat F is communicated with one end of the pipe connector a, the other end of the pipe connector a is communicated with one end of the short pipe through the nut C, the other end of the short pipe is communicated with the pipe connector b through the nut D, and the pipe connector b is communicated with the air inlet which is horizontally arranged on the shell, so that the cavity A is communicated with the combustion chamber, the air pressure of the cavity A is ensured to be the same as the air pressure in the combustion chamber behind the gas compressor, and the mounting seat is communicated with the air inlet at the upper part of the starting valve device.
The invention has the beneficial effects that: on an engine which does not work, the pressure of the cavity A is equal to the pressure of the cavity B, the pressure difference between the cavity A and the cavity B is zero, the piston rod is extruded to the uppermost position of the cavity A by the spring, the valve is separated from the air inlet of the outer sleeve, so that the starting valve is opened, the air channel is in an open state at the moment, the valve is in a state far away from the gas collection cavity C, the gas flow in the gas collection cavity C cannot be blocked, the front-stage surge is improved, and the surge cannot occur when the flow quantity of the gas flow is large.
Drawings
FIG. 1 is a schematic structural view of a starting valve device of the present invention installed in an open exhaust state with an aircraft engine installed;
in the figure: 1-mounting base E; 2-stud; 3-nut F; 4-screws; 5-coating the outer sleeve; 6-cone; 7-a valve; 8-nut E; 9-a housing; 10-a spring; 11-a piston rod; 12-a sealing ring; 13-pipe connector b; 14-nut D; 15-a pin; 16-short pipe; 17-nut C; 18-tube connector a; 19-mount F.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
As shown in fig. 1.
The invention relates to a mounting structure of an automatic locking starting valve device on an aircraft engine, which comprises:
the mounting seat E1 is mounted outside a casing gas collecting cavity C of the high-pressure compressor, and the mounting seat E1 is mounted outside the casing gas collecting cavity C of the high-pressure compressor;
the starting valve device is arranged on the mounting seat E1, when in an open state, the valve 7 of the starting valve device is in a state of being far away from the inside of the gas collecting cavity C, and the gas collecting cavity C is communicated with a lower gas inlet of the starting valve device;
the mounting seat F19 of the combustion chamber casing is positioned behind the high-pressure compressor, and the mounting seat 19 is communicated with the air inlet at the upper part of the starting valve device;
when the starting or slow-moving vehicle is started, air in a combustion chamber entering an air inlet at the upper part of a starting valve device through a mounting seat F19 and air pressure of a gas collecting cavity C of a high-pressure compressor entering the lower part of the starting valve device through a mounting seat E1 form pressure difference, when the pressure difference is not enough to overcome the elasticity of a spring 10 of the starting valve device, the starting valve device is in an open state, at the moment, a valve 7 of the starting valve device is in a state far away from the gas collecting cavity C, the problem that the valve in the prior art can block airflow flowing of the gas collecting cavity is solved, the front-stage surge effect is improved, and the surge phenomenon cannot occur when the airflow flowing quantity is large.
The starting shutter device includes:
the middle part of the bottom surface of the outer sleeve 5 is provided with an air inlet communicated with the air collecting cavity C;
the cone 6 and the shell 9 are sequentially arranged along the circumferential direction of the outer sleeve 5 through positioning of a pin 15 and fixing of a screw 4, and the cone 6 is positioned between the outer sleeve 5 and the shell 9; the upper part of the cone 6 and the shell 9 form a cavity, the lower part of the cone 6 and the jacket 5 form a cavity, vent holes which are correspondingly communicated are arranged on the cone 6 and the shell 9 which are close to the joint of the cone 6 and the jacket 5, and gas can flow from the gas collection cavity C to the vent holes and is discharged out of the bypass;
the piston rod 11 is T-shaped, the small end of the piston rod 11 can slidably penetrate through the middle of the cone 6 and is fixedly screwed with the valve 7 through a nut E8, the valve 7 is driven to be in conical surface tight contact with the air inlet of the outer sleeve 5 after the piston rod 11 slides downwards, the air channel is in a closed state at the moment, the valve 7 is driven to be separated from the air inlet of the outer sleeve 5 after the piston rod 11 slides upwards, and the air channel is in an open state at the moment;
the large end of the piston rod 11 is in slidable close contact with the inner wall of a cavity formed by the cone 6 and the shell 9 through a sealing ring 12, and the large end of the piston rod 11 divides the cavity formed by the cone 6 and the shell 9 into an upper cavity A and a lower cavity B;
a through hole for gas to enter and exit is arranged on the cone 6 at the part shielded by the valve 7, so that the cavity B is communicated with the gas collection cavity C;
the spring 10 with the upper end and the lower end respectively contacted with the large end of the piston rod 11 and the cone 6 is sleeved outside the small end of the piston rod 11, the spring 10 is always positioned in the cavity B when elastically deforming, and the pressure difference between the cavity A and the cavity B drives the piston rod 11 to overcome the elasticity of the spring 10 to slide up and down;
the upper part of the shell 9 is provided with a horizontal air inlet which is communicated with the cavity A.
The mounting seat E1 outside the gas collecting cavity C of the high-pressure compressor casing is fixedly connected with the bottom surface of the outer sleeve 5 through a nut F3 and a stud 2, and the gas collecting cavity C is correspondingly communicated with the lower gas inlet of the outer sleeve 5 of the starting valve device, so that the gas collecting cavity C is communicated with the lower gas inlet of the starting valve device; the gas in the gas collecting cavity C can enter the cavity B from the lower part of the cone 6 and the outer sleeve 5 to form a cavity, so that the pressure of the cavity B is the same as the air pressure of the gas collecting cavity C of the high-pressure compressor casing; or so that the gas in the gas collection chamber C can exit the bypass through the vent holes in the cone 6 and housing 9 near the connection with the jacket 5.
The mounting seat F19 of the combustion chamber casing is communicated with one end of a pipe connector a18, the other end of the pipe connector a18 is communicated with one end of a short pipe 16 through a nut C17, the other end of the short pipe 16 is communicated with a pipe connector b13 through a nut D14, and a pipe connector b13 is communicated with a horizontal air inlet of the shell 9, so that the cavity A is communicated with the combustion chamber, the air pressure of the cavity A is ensured to be the same as the air pressure in the combustion chamber behind the air compressor, and the mounting seat 19 is communicated with the air inlet at the upper part of the starting valve device.
The aircraft engine usually has the requirement of air bleed, several air collecting cavities are arranged in the middle of the high-pressure compressor, the starting valve device of the invention is arranged at the position of the air collecting cavity C, the outer side of the air collecting cavity C is provided with a hole corresponding to the valve 7 of the starting valve device, and the starting valve device is communicated with an air inlet formed by a middle hole of the outer sleeve 5 through the hole.
The shutter 7, the nut E8, the piston rod 11 and the sealing ring 12 can move synchronously, collectively referred to as the start shutter. The movement of the trigger valve is effected by the pressure difference between the chambers a and B and the spring force of the spring 10. The pressure of the cavity A is from the airflow at the outlet of the high-pressure compressor after passing through the diffuser of the combustion chamber, and the pressure of the cavity B is from the airflow of the gas collection cavity C of the high-pressure compressor. On an engine which does not work, the pressure of the cavity A is equal to that of the cavity B, the pressure difference between the cavity A and the cavity B is zero, the piston rod 11 is extruded to the uppermost position of the cavity A by the spring 10, the valve 7 is separated from the air inlet of the outer sleeve 5, then the starting valve is opened, the air channel is in an open state at the moment, the valve 7 is in a state far away from the air collecting cavity C, the gas flow in the air collecting cavity C cannot be blocked, the front-stage surge is improved, and the surge cannot occur when the flow quantity of the air flow is large. When the pressure difference is not enough to overcome the elasticity of the spring 10 to move the starting valve to the matching position of the outer sleeve 5, the starting valve is still in an open state, and the gas in the gas collecting cavity C passes through the starting valve device to quickly enter the outer duct according to a flow path shown by an arrow in figure 1.
And when the engine enters a slow-speed state, the pressure difference between the cavity A and the cavity B overcomes the elasticity of the spring 10, the starting valve moves downwards to the matching position of the outer sleeve 4, and the valve 7 is in close conical surface contact with the air inlet of the outer sleeve 5, so that the middle-stage gas collecting cavity C of the high-pressure compressor is closed to discharge gas. The starting flap then remains closed in all operating states of the engine as the rotational speed continues to increase. When the engine is stopped, the starting shutter is opened in the reverse order.
The starting valve device of the invention has the function that when the starting valve device is started, partial air of the middle stage of the high-pressure air compressor is discharged to the outer duct of the engine until the engine enters a slow-speed state. The purpose of the bleed is to ensure a reliable engine start and to enter a slow vehicle condition.
The starting valve device of the invention realizes automatic locking under the action that the pressure difference between the cavity A and the cavity B overcomes the elasticity of the spring 10, namely when the engine enters a slow vehicle state, the starting valve is automatically closed, and the air release is cut off. The control element of the starting valve device of the invention is the pressure difference of the cavity A and the cavity B. When the engine enters a slow-speed vehicle state, the downward pressure generated by the pressure difference of the cavity A and the cavity B on the starting valve can overcome the elastic force generated after the spring 10 is compressed, the compression amount of the spring 10 is consistent with the stroke of the valve 7 of the starting valve and the outer sleeve 5 from full opening to closing, and the starting valve can be closed.
Claims (10)
1. An installation structure of an automatically-locked starting valve device on an aircraft engine, characterized by comprising:
the mounting seat E (1) is mounted outside a casing gas collecting cavity C of the high-pressure compressor;
the starting valve device is arranged on the mounting seat E (1), and when the valve (7) is in an open state and deflates, the starting valve device is far away from the inside of the gas collecting cavity C, and the gas collecting cavity C is communicated with a lower gas inlet of the starting valve device;
and the mounting seat F (19) of the combustion chamber casing is communicated with the air inlet at the upper part of the starting valve device, and the mounting seat (19) is communicated with the air inlet at the upper part of the starting valve device.
2. A mounting structure of an automatically latching starting shutter device on an aircraft engine according to claim 1, characterized in that: the starting shutter device includes:
the middle part of the bottom surface of the outer sleeve (5) is provided with an air inlet communicated with the air collecting cavity C;
the cone (6) and the shell (9) are sequentially and fixedly installed with the outer sleeve (5) in the circumferential direction, and the cone (6) is located between the outer sleeve (5) and the shell (9); the upper part of the cone (6) and the shell (9) form a cavity, the lower part of the cone (6) and the outer sleeve (5) form a cavity, vent holes which are correspondingly communicated are formed in the cone (6) and the shell (9) which are close to the joint of the cone (6) and the outer sleeve (5), and gas can flow from the gas collection cavity C to the vent holes and is discharged out of the outer duct;
the small end of the piston rod (11) can slidably penetrate through the middle of the cone (6) and is fixedly provided with the valve (7), the piston rod (11) slides downwards to drive the valve (7) to be in conical surface tight contact with the air inlet of the outer sleeve (5), the air passage is closed at the moment, the piston rod (11) slides upwards to drive the valve (7) to be separated from the air inlet of the outer sleeve (5), and the air passage is opened at the moment;
the large end of the piston rod (11) is in slidable close contact with the inner wall of a cavity formed by the cone (6) and the shell (9), and the large end of the piston rod (11) divides the cavity formed by the cone (6) and the shell (9) into an upper cavity A and a lower cavity B;
a cone (6) positioned at the part shielded by the valve (7) is provided with a through hole for gas to enter and exit, so that the cavity B is communicated with the gas collection cavity C;
a spring (10) with the upper end and the lower end respectively contacted with the large end of the piston rod (11) and the cone (6) is sleeved outside the small end of the piston rod (11), the spring (10) is always positioned in the cavity B when elastically deformed, and the pressure difference between the cavity A and the cavity B drives the piston rod (11) to overcome the elasticity of the spring (10) to slide up and down;
the upper part of the shell (9) is provided with a horizontal air inlet communicated with the cavity A.
3. A mounting structure of an automatically latching starting shutter device on an aircraft engine according to claim 2, characterized in that: the cone (6), the shell (9) and the outer sleeve (5) are sequentially and fixedly installed through pin (15) positioning and screw (4).
4. A mounting structure of an automatically latching starting shutter device on an aircraft engine according to claim 2, characterized in that: the piston rod (11) is T-shaped.
5. A mounting structure of an automatically latching starting shutter device on an aircraft engine according to claim 2, characterized in that: the periphery of the large end of the piston rod (11) is provided with a sealing ring (12) which is in slidable close contact with the inner wall of a cavity formed by the cone (6) and the shell (9).
6. A mounting structure of an automatically latching starting shutter device on an aircraft engine according to claim 2, characterized in that: the small end of the piston rod (11) penetrating through the middle of the cone (6) is screwed and fixed with the valve (7) through a nut E (8).
7. A mounting structure of an automatically latching starting shutter device on an aircraft engine according to claim 2, characterized in that: the mounting seat E (1) is fixedly connected with the bottom surface of the outer sleeve (5), the gas collecting cavity C is correspondingly communicated with a lower air inlet of the outer sleeve (5) of the starting valve device, and the gas collecting cavity C is communicated with a lower air inlet of the starting valve device.
8. The mounting structure of an automatically latching starting shutter device on an aircraft engine as claimed in claim 7, characterized in that: the mounting seat E (1) is fixedly connected with the bottom surface of the outer sleeve (5) through a nut F (3) and a stud (2).
9. Mounting structure of an automatically latching starting shutter device on an aircraft engine according to claim 2 or 8, characterized in that: the mounting seat F (19) is communicated with a horizontal air inlet of the shell (9) through a short pipe (16).
10. A mounting structure of an automatically latching start shutter device on an aircraft engine according to claim 9, characterized in that: the mounting seat F (19) is communicated with one end of a pipe connector a (18), the other end of the pipe connector a (18) is communicated with one end of a short pipe (16) through a nut C (17), the other end of the short pipe (16) is communicated with a pipe connector b (13) through a nut D (14), and the pipe connector b (13) is communicated with a horizontal air inlet of the shell (9), so that the cavity A is communicated with the combustion chamber at the same air pressure, and the mounting seat (19) is communicated with an air inlet at the upper part of the starting valve device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110943037.8A CN113606042A (en) | 2021-08-17 | 2021-08-17 | Mounting structure of automatically-locked starting valve device on aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110943037.8A CN113606042A (en) | 2021-08-17 | 2021-08-17 | Mounting structure of automatically-locked starting valve device on aircraft engine |
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| CN113606042A true CN113606042A (en) | 2021-11-05 |
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| CN202110943037.8A Pending CN113606042A (en) | 2021-08-17 | 2021-08-17 | Mounting structure of automatically-locked starting valve device on aircraft engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114458455A (en) * | 2021-12-27 | 2022-05-10 | 中国航发长春控制科技有限公司 | High-reliability high-temperature-resistant high-pressure-resistant dynamic sealing structure |
| CN114483322A (en) * | 2021-12-29 | 2022-05-13 | 中国航发长春控制科技有限公司 | Aeroengine starts bleed device with temperature compensation function |
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| US20070193274A1 (en) * | 2006-02-21 | 2007-08-23 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
| CN202746018U (en) * | 2012-08-06 | 2013-02-20 | 沈阳黎明航空发动机(集团)有限责任公司 | Air discharging valve structure for heavy duty gas turbine |
| CN204476567U (en) * | 2015-01-04 | 2015-07-15 | 中国航空工业集团公司沈阳发动机设计研究所 | It is a kind of that for monitoring, engine interior is total, the bleed mechanism of static pressure pressure ratio signal |
| CN105952540A (en) * | 2016-05-25 | 2016-09-21 | 中国科学院工程热物理研究所 | Stable working margin adjusting system of multistage compressor |
| CN206513443U (en) * | 2017-01-23 | 2017-09-22 | 中国航发沈阳发动机研究所 | A kind of engine bleed pipe and the engine with it |
| CN108035810A (en) * | 2017-11-06 | 2018-05-15 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Pressure-regulating device before a kind of air turbine starter stage of turbine |
| FR3079875A1 (en) * | 2018-04-05 | 2019-10-11 | Safran Aircraft Engines | TURBOMACHINE DISCHARGE DEVICE COMPRISING A VALVE |
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| CN114458455A (en) * | 2021-12-27 | 2022-05-10 | 中国航发长春控制科技有限公司 | High-reliability high-temperature-resistant high-pressure-resistant dynamic sealing structure |
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| CN114483322A (en) * | 2021-12-29 | 2022-05-13 | 中国航发长春控制科技有限公司 | Aeroengine starts bleed device with temperature compensation function |
| CN114483322B (en) * | 2021-12-29 | 2023-09-19 | 中国航发长春控制科技有限公司 | Aeroengine starting air entraining device with temperature compensation function |
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