CN105736148A - Gunpowder starting device of aircraft engine - Google Patents
Gunpowder starting device of aircraft engine Download PDFInfo
- Publication number
- CN105736148A CN105736148A CN201610090455.6A CN201610090455A CN105736148A CN 105736148 A CN105736148 A CN 105736148A CN 201610090455 A CN201610090455 A CN 201610090455A CN 105736148 A CN105736148 A CN 105736148A
- Authority
- CN
- China
- Prior art keywords
- engine
- gas injection
- aero
- rotating shaft
- electric
- 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.)
- Pending
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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
- F02C7/26—Starting; Ignition
Abstract
The invention relates to a gunpowder starting device of an aircraft engine. The starting device is arranged on a propeller rotating shaft, and the propeller rotating shaft is connected with the engine; combustion chambers which are evenly distributed are arranged in the starting device and are connected with gas injection holes; gas gunpowder columns are arranged in the combustion chambers, and an electric initiator is arranged on one side, close to the corresponding gas injection hole, of each gas gunpowder column and is connected with an electric connector; and the electric connectors are electric brush type electric connectors, contact is good, work is reliable, maintenance is convenient, and the outlet directions of the gas injection holes are opposite to the rotating directions of the propeller rotating shaft; and the number of the combustion chambers is four, and the gas injection holes are of shrinkage and expansion structures. The gunpowder starting device of the aircraft engine has the beneficial effects of being simple in structure, reliable in work, convenient to maintain, small in weight, small in power consumption amount and capable of adapting to various launching environments.
Description
Technical field
The invention belongs to engine starting techniques field, particularly relate to the cartridge start device of a kind of aero-engine.
Background technology
Aero-engine is generally adopted and pulls Suo Qidong, motor belt motor turns starting or windmilling startup.It is simple and convenient for pulling Suo Qidong advantage, but requires that aircraft ground starts, it is impossible to meet the start request of empty emitting aircraft.It is strong adaptability that motor belt motor turns starting advantage, but structure is complicated, and on the one hand motor belt motor turns and needs to consume a large amount of electric energy, thus it requires design greater power power supply, on the other hand, motor component makes whole machine weight increase, and is unfavorable for aircraft loss of weight.Carrier aircraft flight speed is then had certain requirement by windmilling startup, it is clear that can not meet the carrier aircraft of low-speed operations and the requirement of ground-launched aircraft.
Summary of the invention
It is an object of the invention to for above-mentioned deficiency and defect, it is provided that a kind of simple in construction, lightweight, power consumption is little, and is adapted to the cartridge start device of the aero-engine of various launch environment.
The present invention is achieved through the following technical solutions above-mentioned purpose:
A kind of cartridge start device of aero-engine, wherein: launcher is arranged in propeller rotating shaft, propeller rotating shaft is connected with electromotor, equally distributed combustor it is provided with inside launcher, described combustor is connected with gas injection hole, being provided with combustion gas powder column in described combustor, be provided with electric initiator at combustion gas powder column near the side of gas injection hole, electric initiator is connected with electric connector.
The cartridge start device of a kind of aero-engine, wherein: electric connector is electric brush type electric connector, contact is good, and reliable operation is easy to maintenance.
A kind of cartridge start device of aero-engine, wherein: gas injection hole Way out is in opposite direction with propeller axis of rotation.
A kind of cartridge start device of aero-engine, wherein: described combustor is 4.
A kind of cartridge start device of aero-engine, wherein: gas injection hole is shrinkage expansion structure.
The invention have the advantage that simple in construction, reliable operation, easy to maintenance, lightweight, power consumption is little, and is adapted to the engine starting gear of various launch environment.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram of the cartridge start device of a kind of aero-engine of the present invention；
Fig. 2 is the partial structurtes schematic diagram of the cartridge start device of a kind of aero-engine of the present invention；
Fig. 3 is the partial sectional view of the cartridge start device of a kind of aero-engine of the present invention.
Accompanying drawing labelling: launcher 1, combustor 2, combustion gas powder column 3, gas injection hole 4, electric initiator 5, electric connector 6, electromotor 7, propeller rotating shaft 8.
Detailed description of the invention
Embodiment 1, a kind of aero-engine cartridge start device, wherein: launcher 1 is arranged in propeller rotating shaft 8, propeller rotating shaft 8 is connected with electromotor 7, launcher 1 is internal is provided with equally distributed combustor 2, described combustor 2 is connected with gas injection hole 4, being provided with combustion gas powder column 3 in described combustor 2, be provided with electric initiator 5 at combustion gas powder column 3 near the side of gas injection hole 4, electric initiator 5 is connected with electric connector 6.
Embodiment 2, a kind of aero-engine cartridge start device, wherein: electric connector 6 is electric brush type electric connector, contact is good, and reliable operation is easy to maintenance.All the other are with embodiment 1.
Embodiment 3, a kind of aero-engine cartridge start device, wherein: gas injection hole 4 Way out is contrary with propeller rotating shaft 8 rotation direction.All the other are with embodiment 1.
Embodiment 4, a kind of aero-engine cartridge start device, wherein: described combustor 2 is 4.All the other are with embodiment 1.
Embodiment 5, a kind of aero-engine cartridge start device, wherein: gas injection hole 4 is shrinkage expansion structure.All the other are with embodiment 1.
The operation principle of the cartridge start device of a kind of aero-engine of the present invention:
Powered to electric initiator 5 by electric connector 6, electric initiator 5 ignites combustion gas powder column 3, and the high-pressure gas that combustion gas powder column 3 produces sprays from gas injection hole 4, and its counteracting force promotes launcher 1, thus carrying screws rotating shaft 8 high speed rotating, and then realize electromotor 7 and start.
Claims (5)
1. the cartridge start device of an aero-engine, it is characterized in that: launcher (1) is arranged in propeller rotating shaft (8), propeller rotating shaft (8) is connected with electromotor (7), launcher (1) is internal is provided with equally distributed combustor (2), described combustor (2) is connected with gas injection hole (4), it is provided with combustion gas powder column (3) in described combustor (2), being provided with electric initiator (5) at combustion gas powder column (3) near the side of gas injection hole (4), electric initiator (5) is connected with electric connector (6).
2. the cartridge start device of a kind of aero-engine as claimed in claim 1, it is characterised in that: electric connector (6) is electric brush type electric connector.
3. the cartridge start device of a kind of aero-engine as claimed in claim 1, it is characterised in that gas injection hole (4) Way out is contrary with propeller rotating shaft (8) rotation direction.
4. the cartridge start device of a kind of aero-engine as claimed in claim 1, it is characterised in that: described combustor (2) is 4.
5. the cartridge start device of a kind of aero-engine as claimed in claim 1, it is characterised in that: gas injection hole (4) is shrinkage expansion structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610090455.6A CN105736148A (en) | 2016-02-18 | 2016-02-18 | Gunpowder starting device of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610090455.6A CN105736148A (en) | 2016-02-18 | 2016-02-18 | Gunpowder starting device of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105736148A true CN105736148A (en) | 2016-07-06 |
Family
ID=56241980
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610090455.6A Pending CN105736148A (en) | 2016-02-18 | 2016-02-18 | Gunpowder starting device of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105736148A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2356746A (en) * | 1942-02-26 | 1944-08-29 | Homer A Boushey | Jet propulsion device |
| US2474685A (en) * | 1945-04-12 | 1949-06-28 | Stewart Warner Corp | Jet propulsion apparatus |
| FR1076691A (en) * | 1953-05-05 | 1954-10-28 | Plessey Co Ltd | System for starting gas turbines such as those used for propelling projectiles |
| US3077736A (en) * | 1959-03-04 | 1963-02-19 | Olin Mathieson | Gas generating device |
| CN101363387A (en) * | 2008-09-17 | 2009-02-11 | 王学章 | Rotating athodyd |
| CN102889132A (en) * | 2012-10-24 | 2013-01-23 | 哈尔滨东安发动机（集团）有限公司 | Starting device of gas turbine engine |
| CN204041245U (en) * | 2014-08-15 | 2014-12-24 | 中国燃气涡轮研究院 | The nozzle pipe line structure that a kind of powder gas starts |
-
2016
- 2016-02-18 CN CN201610090455.6A patent/CN105736148A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2356746A (en) * | 1942-02-26 | 1944-08-29 | Homer A Boushey | Jet propulsion device |
| US2474685A (en) * | 1945-04-12 | 1949-06-28 | Stewart Warner Corp | Jet propulsion apparatus |
| FR1076691A (en) * | 1953-05-05 | 1954-10-28 | Plessey Co Ltd | System for starting gas turbines such as those used for propelling projectiles |
| US3077736A (en) * | 1959-03-04 | 1963-02-19 | Olin Mathieson | Gas generating device |
| CN101363387A (en) * | 2008-09-17 | 2009-02-11 | 王学章 | Rotating athodyd |
| CN102889132A (en) * | 2012-10-24 | 2013-01-23 | 哈尔滨东安发动机（集团）有限公司 | Starting device of gas turbine engine |
| CN204041245U (en) * | 2014-08-15 | 2014-12-24 | 中国燃气涡轮研究院 | The nozzle pipe line structure that a kind of powder gas starts |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160706 |