CN204041245U - The nozzle pipe line structure that a kind of powder gas starts - Google Patents
The nozzle pipe line structure that a kind of powder gas starts Download PDFInfo
- Publication number
- CN204041245U CN204041245U CN201420462720.5U CN201420462720U CN204041245U CN 204041245 U CN204041245 U CN 204041245U CN 201420462720 U CN201420462720 U CN 201420462720U CN 204041245 U CN204041245 U CN 204041245U
- Authority
- CN
- China
- Prior art keywords
- nozzle
- fitting seat
- powder gas
- air supply
- pipe line
- 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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model belongs to engine starting techniques, relates to the nozzle pipe line structure that a kind of powder gas for motor starts.The nozzle pipe line structure that described powder gas starts comprises fitting seat, fan-shaped endless tube, plug, conical nozzle, nozzle of air supply.Wherein, described fitting seat is welded on turbine casing, except connecting the fitting seat of exterior line, all the other fitting seat import plugs seal, connect into the circulating line of powder gas between each fitting seat with fan-shaped endless tube, on the outer shroud between the blade path of nozzle ring, have conical nozzle, described nozzle of air supply is arranged in fitting seat, and annular pass on turbine casing is communicated with the conical nozzle on guider by the air-flow path on nozzle of air supply.The utility model does not need special starting turbine, forwards motivation, meet the requirements of rotating speed by powder gas moment impact turbine band, and compact structure, reliability is high, has larger actual application value.
Description
Technical field
The utility model belongs to engine starting techniques, the nozzle pipe line structure that the powder gas relating to a kind of motor starts.
Background technique
The starting of the turbofan engine of some purposes, accelerating process have its particularity and complexity, require just can accelerate to high thrust state without slow train warm-up period, and whole accelerating process is generally at 6s ~ 10s.For the turbofan engine of double rotor or triple-spool, the power needed for engine start is comparatively large, also has the mutual interference of slip between each rotor, therefore adopts gunpowder standard to start reliable.And the cartridge start mode of routine needs special starting turbine, size is large, and part is many, poor reliability.
Model utility content
The purpose of this utility model: the utility model provides a kind of compact structure, and reliability is high, the nozzle pipe line structure that the powder gas not needing special starting turbine to meet the requirements of rotating speed starts.
The technical solution of the utility model: the nozzle pipe line structure that a kind of powder gas starts, it comprises fitting seat, fan-shaped endless tube, plug, conical nozzle, nozzle of air supply, wherein, described fitting seat is welded on turbine casing, except connecting the fitting seat of exterior line, all the other fitting seat import plugs seal, connect into the circulating line of powder gas with fan-shaped endless tube between each fitting seat, on outer shroud between the blade path of nozzle ring, have conical nozzle, described nozzle of air supply is arranged in fitting seat, annular pass on turbine casing is communicated with the conical nozzle on guider by the air-flow path on nozzle of air supply.
Described fitting seat quantity is consistent with the conical nozzle be arranged on nozzle ring, for connecting fan-shaped endless tube to form the circulating line of powder gas.
Described nozzle of air supply external cylindrical surface has counterbore, prevents the rotation of nozzle of air supply by being screwed into anti-turn screw on fitting seat.
Conical nozzle on the air-flow path of nozzle of air supply and guider defines one and restrains-the outlet passageway of expansion shape.
Conical nozzle is directly processed between guide vane passage.
The beneficial effects of the utility model: the anti-force type axial flow turbine of turbine pilot jet pipeline to routine of turbofan engine cartridge start of the present utility model blows and turn, the high-temperature high-pressure fuel gas of the gunpowder generator generation of casing outside, by the circulating line on turbine casing, enter the convergence-expansion supersonic nozzle on turbine nozzle vane passage outer shroud, moment impact turbine band forwards motivation, meets the requirements of rotating speed.Through the verification experimental verification of certain h type engine h, motor band can be forwarded to slow train rotating speed in 3 ~ 4 seconds.In addition, compact structure, reliability is high, does not need special starting turbine, has larger actual application value.
Accompanying drawing explanation
The nozzle pipe line structure schematic diagram that a kind of powder gas of Fig. 1 the utility model starts;
Fig. 2 is the partial sectional view of Fig. 1,
Wherein, 1-fitting seat; The fan-shaped endless tube of 2-; 3-plug; 4-anti-turn screw; 5-conical nozzle; 6-turbine casing; 7-nozzle ring; 8-nozzle of air supply.
Embodiment
Below by concrete mode of execution, the utility model is described in further detail:
Please refer to Fig. 1, Fig. 2, wherein, Fig. 1 nozzle pipe line structure schematic diagram that to be the utility model start for the powder gas of motor, Fig. 2 is the partial sectional view of Fig. 1.The nozzle pipe line structure that the utility model powder gas starts comprises fitting seat 1, fan-shaped endless tube 2, plug 3, anti-turn screw 4, conical nozzle 5, nozzle of air supply 8.Described fitting seat 1 is welded on turbine casing 6, and quantity is consistent with the conical nozzle be arranged on nozzle ring, for connecting fan-shaped endless tube to form the circulating line of powder gas.。Except connecting the fitting seat of exterior line, all the other fitting seat import plugs 3 seal, and prevent powder gas from leaking.Connect into the circulating line of powder gas between each fitting seat with fan-shaped endless tube 2, make powder gas by circulating line, enter nozzle of air supply.On outer shroud between the blade path of nozzle ring 7, have conical nozzle 5.Be arranged in fitting seat by nozzle of air supply 8, annular pass on turbine casing is communicated with the conical nozzle on guider by the air-flow path on nozzle of air supply, defines the Laval nozzle of a convergence-expansion, carries out Supersonic acceleration to powder gas.Nozzle of air supply external cylindrical surface has counterbore, prevents the rotation of nozzle of air supply by being screwed into anti-turn screw 4 on fitting seat.
During the nozzle pipe line structure work that the utility model powder gas starts: the gunpowder generator of casing outside produces the powder gas of High Temperature High Pressure, enter in fitting seat by exterior line, then entered into respectively by the circulating line on turbine casing in the nozzle of air supply of circumference distribution.Taper hole on nozzle of air supply and the conical nozzle on nozzle ring define the supersonic nozzle of convergence-expansion, by the physical dimension (comprising the throat dimension of spout, angle, length etc.) of design con-trol conical nozzle, powder gas is accelerated at Supersonic nozzle, and the air-flow (flow outlet Mach number can reach about 1.8) finally sprayed by this nozzle instantaneously (in 3 ~ 4 seconds) impulse turbine band forwards motivation to requiring rotating speed.
Being different from conventional motor cartridge start is in sum design starting turbine, after being arranged in turbine rotor blade, being blown turn starting turbine and drive motor again by powder gas.The utility model is by arranging rational airflow pipeline, by the processing of Supersonic nozzle on the passage outer shroud of guide vane, with guider one, powder gas directly blows rotation leaf, eliminate starting turbine structure, therefore effective simplified structure, improves system reliability, and greatly reduce cost, create larger real economy benefit.
Claims (5)
1. the nozzle pipe line structure of a powder gas starting, it is characterized in that, comprise fitting seat (1), fan-shaped endless tube (2), plug (3), conical nozzle (5), nozzle of air supply (8), wherein, described fitting seat (1) is welded on turbine casing (6), except connecting the fitting seat of exterior line, all the other fitting seat imports plug (3) seals, connect into the circulating line of powder gas with fan-shaped endless tube (2) between each fitting seat, on outer shroud between the blade path of nozzle ring (7), have conical nozzle (5), described nozzle of air supply (8) is arranged in fitting seat, annular pass on turbine casing is communicated with the conical nozzle on guider by the air-flow path on nozzle of air supply.
2. the nozzle pipe line structure of powder gas starting according to claim 1, it is characterized in that, described fitting seat (1) quantity is consistent with the conical nozzle be arranged on nozzle ring, for connecting fan-shaped endless tube to form the circulating line of powder gas.
3. the nozzle pipe line structure of powder gas starting according to claim 1, it is characterized in that, described nozzle of air supply external cylindrical surface has counterbore, prevents the rotation of nozzle of air supply by being screwed into anti-turn screw (4) on fitting seat.
4. the nozzle pipe line structure that starts of powder gas according to claim 1, is characterized in that, the conical nozzle on the air-flow path of nozzle of air supply and guider defines one and restrains-the outlet passageway of expansion shape.
5. the nozzle pipe line structure of powder gas starting according to claim 1, it is characterized in that, conical nozzle is directly processed between guide vane passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420462720.5U CN204041245U (en) | 2014-08-15 | 2014-08-15 | The nozzle pipe line structure that a kind of powder gas starts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420462720.5U CN204041245U (en) | 2014-08-15 | 2014-08-15 | The nozzle pipe line structure that a kind of powder gas starts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204041245U true CN204041245U (en) | 2014-12-24 |
Family
ID=52241917
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420462720.5U Active CN204041245U (en) | 2014-08-15 | 2014-08-15 | The nozzle pipe line structure that a kind of powder gas starts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204041245U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736148A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Gunpowder starting device of aircraft engine |
| CN106481457A (en) * | 2016-10-28 | 2017-03-08 | 西安近代化学研究所 | A kind of solid gas starter |
| CN108167080A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | A kind of fanjet startup combustor structure |
| CN108590863A (en) * | 2018-03-05 | 2018-09-28 | 中国北方发动机研究所(天津) | A kind of adaptive inlet duct of missile turbojet engine cartridge start |
| CN108590864A (en) * | 2018-03-05 | 2018-09-28 | 中国北方发动机研究所(天津) | A kind of small-sized missile turbojet engine cartridge start method and device |
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN110714838A (en) * | 2019-11-01 | 2020-01-21 | 北京动力机械研究所 | Turbojet engine started by gas |
| CN115523032A (en) * | 2022-10-12 | 2022-12-27 | 常州环能涡轮动力股份有限公司 | Quick start structure of turbojet engine |
-
2014
- 2014-08-15 CN CN201420462720.5U patent/CN204041245U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736148A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Gunpowder starting device of aircraft engine |
| CN106481457A (en) * | 2016-10-28 | 2017-03-08 | 西安近代化学研究所 | A kind of solid gas starter |
| CN108167080A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | A kind of fanjet startup combustor structure |
| CN108167080B (en) * | 2017-11-20 | 2019-05-10 | 北京动力机械研究所 | A kind of fanjet startup combustor structure |
| CN108590863A (en) * | 2018-03-05 | 2018-09-28 | 中国北方发动机研究所(天津) | A kind of adaptive inlet duct of missile turbojet engine cartridge start |
| CN108590864A (en) * | 2018-03-05 | 2018-09-28 | 中国北方发动机研究所(天津) | A kind of small-sized missile turbojet engine cartridge start method and device |
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN110714838A (en) * | 2019-11-01 | 2020-01-21 | 北京动力机械研究所 | Turbojet engine started by gas |
| CN115523032A (en) * | 2022-10-12 | 2022-12-27 | 常州环能涡轮动力股份有限公司 | Quick start structure of turbojet engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204041245U (en) | The nozzle pipe line structure that a kind of powder gas starts | |
| CN109668739B (en) | Test platform for multi-duct turbine nozzle integrated research | |
| CN106065830B (en) | A kind of pulse detonation combustor device combined based on rotary valve with pneumatic operated valve | |
| WO2021243949A1 (en) | Gas turbine power generation device using viscous force to convert pulse detonation gas energy | |
| AU2014343563B2 (en) | Axial fluid machine and method for power extraction | |
| CN204663701U (en) | A kind of exhaust mixer of turbofan engine | |
| CN107100681A (en) | Secondary system for gas-turbine unit | |
| JP2012140960A (en) | Thrust augmented gas turbine engine | |
| CN103597195A (en) | Tail cone for a microjet rotary turbine engine | |
| CN212406895U (en) | Pulse detonation combustion gas turbine power generation device combined with viscous turbine | |
| CN209539463U (en) | A kind of turbine rotor wheel rim seal structure | |
| CN103726953A (en) | Turbofan engine with reverse ducts | |
| CN103726952B (en) | Shunting gas-turbine unit | |
| CN107763071A (en) | Composite bearing and method of work | |
| CN104234867A (en) | Scramjet engine | |
| CN214787743U (en) | Jet engine with contra-rotating combined rotor | |
| CN112179605B (en) | Ejector nozzle experimental device for simulating outflow of aircraft | |
| CN203275094U (en) | Variable-length ultrasonic diffuser | |
| CN104131915A (en) | Ramjet started in static state | |
| CN204941721U (en) | A kind of pressed engine with pulsation combustion room | |
| CN204060937U (en) | A kind of aeroengine | |
| CN203685300U (en) | Rotary jet stator recoil turbine | |
| CN102606341B (en) | The method retired plane being made into combustion engine and the combustion engine using the method to make into | |
| CN114623019B (en) | Large-bypass-ratio split type variable-circulation turbofan engine | |
| CN212027941U (en) | Pulse detonation engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: No. 999, Xuefu Road, Xindu, Chengdu, Sichuan 610500 Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 Jiangyou 305 mailbox operation monitoring department, Mianyang City, Sichuan Province Patentee before: CHINA GAS TURBINE EST |