CN102889132A - Starting device of gas turbine engine - Google Patents
Starting device of gas turbine engine Download PDFInfo
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- CN102889132A CN102889132A CN2012104091034A CN201210409103A CN102889132A CN 102889132 A CN102889132 A CN 102889132A CN 2012104091034 A CN2012104091034 A CN 2012104091034A CN 201210409103 A CN201210409103 A CN 201210409103A CN 102889132 A CN102889132 A CN 102889132A
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- starting
- starter
- gas turbine
- turbine engine
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a starting device of a gas turbine engine. The starting device comprises a stator, a starting turbine impeller and a gunpowder starting device. The starting turbine impeller is fixedly connected with a turbine rotor; the starting turbine impeller is provided with uniformly-distributed axial tensile blades; and a spraying nozzle body of the gunpowder starting device is provided with tangential spraying openings which are uniformly distributed in a manner of being opposite to the axial tensile blades on the starting turbine impeller. According to the starting device, an auxiliary piece transmission part is saved, the radial size is not increased and the starting device has the characteristics of small volume and light weight. Gunpowder can be used for one time to meet the characteristic of starting the gas turbine engine for a bullet for one time, and the actual use effect is good.
Description
Technical field
The present invention relates to a kind of starting arrangement, especially a kind of starting arrangement of gas turbine engine.
Background technique
When gas turbine engine is started working, need to utilize extraneous energy that rotor is rotated, through a starting process, just can enter stable idle power rating.Start mode commonly used has following three kinds: the starting of (1) electric starter is with the power supply on the motor or ground power supply drive motor or starter generator, and motor or starter generator drive engine rotor by the transmission shaft on the accessory drive parts.The advantage of electric starter is to use simply, the starting process full automation, and starter motor mechanism is less, and is simple in structure, and cost is low, and is easy to maintenance; Shortcoming is that not only motor itself is heavy, but also must adopt than the several-fold storage battery of self weight, and simultaneously, the power of the starter motor to external world change of temperature and voltage own is very responsive.(2) without the starting of the turbo-starter of gas compressor formula, be to blow impact wheel by gunpowder or the burning of other chemical fuel or pressurized air, drive engine rotor by the transmission shaft on the turbine drives accessory drive parts again.This starter motor has good starting characteristic, and the starting time is short, and starting power is large, and shortcoming is that volume is large, weight large, number of starts is subject to the gunpowder quantitative limitation.(3) gas turbine starter starting, to drive large gas turbine engine with little gas turbine engine, and little gas turbine starter also needs starting, its start mode mainly adopts electricity starting or without the turbo-starter starting of gas compressor, the advantage of this starter motor is to have larger starting power, can guarantee the starting of high thrust motor, and do not rely on ground installation, repeatedly re-lighting, shortcoming is complex structure, owing to starting and the time for acceleration of starter motor itself, prolonged the starting time of motor.
For certain bullet gas turbine engine, it is wanted, and cube is little, quality is light, and disposable starting, consider the pluses and minuses of above starter motor, be more suitable for than all the other dual modes without the turbo-starter of gas compressor formula, but existing design without the gas compressor formula is for repeatedly starting, and need to drive engine rotor by the transmission shaft on the accessory drive parts, structure is still complicated, and volume is large, is not suitable for the starting that bullet is used motor.
Summary of the invention
The objective of the invention is to design a kind of bullet with the starting arrangement of gas turbine engine, satisfy the characteristics that its volume is little, quality is light, and requirement that can disposable starting.
Concrete technological scheme of the present invention is: the starting arrangement of gas turbine engine comprises stator, starting turbine impeller and cartridge start device.Described starting turbine impeller is fixedly connected with turbine rotor, the starting turbine impeller is provided with uniform axial tension blade, the cartridge start device comprises pyrotechnics starter cone and the starter nozzle body of installing on it and is installed on the stator, the starter cone links to each other with cavity in the starter nozzle body, be provided with the uniform tangential spout that communicates with internal cavities on the described starter nozzle body, described tangential spout faces the axial tension blade on the starting turbine impeller, in the cavity in the starter cone gunpowder and ignition mechanism are housed, described starting turbine impeller and stator radial seal also are provided with the axial diversion blade on the described stator.Described radial seal structure is the sealing of comb tooth, namely is provided with the comb tooth on the starting turbine impeller, is provided with seal coating on the stator, and described axial tension blade is the 40-60 sheet, is preferably 56; Tangential spout on the described starter nozzle is 4-10, is preferably 8.
Axial diversion impeller clearance and starter cone gabarit between starter nozzle body gabarit of the present invention, stator, stator have formed an air flow channel.When work, by the ignition mechanism in the starter cone gunpowder is lighted, the high temperature and high pressure gas that gunpowder produces blows out at a high speed by the tangential spout of starter nozzle body, impact the axial tension blade on the corresponding starting turbine impeller of tangential spout, make the starting turbine vane rotary, rotor driven reaches the needed rotating speed of motor, thus the starting gas turbine engine.The gas of High Temperature High Pressure discharges by the axial diversion impeller clearance on the stator at last.
Starting arrangement of the present invention has been cancelled the accessory drive parts, and ignition starting apparatus is installed in engine shaft upwards, by lighting gunpowder across-the-line starting gas turbine engine, does not increase radial dimension, has a volume little, the characteristics that quality is light.The characteristics that bullet is used the disposable starting of gas turbine engine are satisfied in the disposable use of gunpowder, and practical effect is good.
Description of drawings
Fig. 1 is structural representation of the present invention;
Fig. 2 is schematic diagram of the present invention;
Fig. 3 is the partial sectional view of Fig. 1.
Embodiment
As shown in the figure, the starting arrangement of gas turbine engine comprises stator 1, starting turbine impeller 3 and cartridge start device.Described starting turbine impeller 3 is fixedly connected with turbine rotor 4, starting turbine impeller 3 is provided with uniform axial tension blade 2, the cartridge start device comprises pyrotechnics starter cone 8 and the starter nozzle body 9 of installing on it and is installed on the stator 1, cavity in starter cone 8 and the starter nozzle body 9 links to each other, be provided with the uniform tangential spout 5 that communicates with internal cavities on the described starter nozzle body 9, described tangential spout 5 faces the axial tension blade 2 on the starting turbine impeller 3, in the cavity in the starter cone 8 gunpowder 7 and ignition mechanism 6 are housed, described starting turbine impeller 3 and stator 1 radial seal also are provided with axial diversion blade 10 on the described stator 1.
Claims (6)
1. the starting arrangement of a gas turbine engine, it is characterized in that, the starting arrangement of gas turbine engine comprises stator (1), starting turbine impeller (3) and cartridge start device, described starting turbine impeller (3) is fixedly connected with turbine rotor (4), starting turbine impeller (3) is provided with uniform axial tension blade (2), the cartridge start device comprises pyrotechnics starter cone (8) and the starter nozzle body (9) installed on it and being installed on the stator (1), cavity in starter cone (8) and the starter nozzle body (9) links to each other, be provided with the uniform tangential spout (5) that communicates with internal cavities on the described starter nozzle body (9), described tangential spout (5) faces the axial tension blade (2) on the starting turbine impeller (3), in the cavity in the starter cone (8) gunpowder (7) and ignition mechanism (6) are housed, described starting turbine impeller (3) and stator (1) radial seal also are provided with axial diversion blade (10) on the described stator (1).
2. the starting arrangement of gas turbine engine as claimed in claim 1 is characterized in that, described radial seal structure is the sealing of comb tooth, namely is provided with comb tooth (11) on the starting turbine impeller (3), is provided with seal coating (12) on the stator (1).
3. the starting arrangement of gas turbine engine as claimed in claim 1 is characterized in that, described axial tension blade (2) is the 40-60 sheet.
4. such as the starting arrangement of gas turbine engine as described in claim 1 or 3, it is characterized in that, described axial tension blade (2) is 56.
5. the starting arrangement of gas turbine engine as claimed in claim 1 is characterized in that, the tangential spout (5) on the described starter nozzle is 4-10.
6. such as the starting arrangement of gas turbine engine as described in claim 1 or 5, it is characterized in that, the tangential spout (5) on the described starter nozzle is 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210409103.4A CN102889132B (en) | 2012-10-24 | 2012-10-24 | The launcher of gas-turbine unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210409103.4A CN102889132B (en) | 2012-10-24 | 2012-10-24 | The launcher of gas-turbine unit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102889132A true CN102889132A (en) | 2013-01-23 |
| CN102889132B CN102889132B (en) | 2016-09-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210409103.4A Active CN102889132B (en) | 2012-10-24 | 2012-10-24 | The launcher of gas-turbine unit |
Country Status (1)
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| CN (1) | CN102889132B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105179087A (en) * | 2015-09-13 | 2015-12-23 | 张宗贤 | Power device with gunpowder combustion jet function |
| 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 |
| CN106458323A (en) * | 2014-04-03 | 2017-02-22 | 赛峰直升机发动机公司 | Drive chain for a helicopter incorporating a pyrotechnic assistance drive module and helicopter comprising same |
| 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 |
| CN109306901A (en) * | 2017-07-26 | 2019-02-05 | 和谐工业有限责任公司 | Air turbine engine-starters |
| CN110062841A (en) * | 2016-11-18 | 2019-07-26 | 赛峰直升机发动机公司 | Pyrotechnic |
| CN110714838A (en) * | 2019-11-01 | 2020-01-21 | 北京动力机械研究所 | Turbojet engine started by gas |
| CN112576378A (en) * | 2020-12-14 | 2021-03-30 | 江西洪都航空工业集团有限责任公司 | Gas turbine engine with automatic separation starting turbine |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106481457B (en) * | 2016-10-28 | 2017-11-24 | 西安近代化学研究所 | A kind of solid gas starter |
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| US20040234369A1 (en) * | 2003-05-19 | 2004-11-25 | Feest Robert H. | Air turbine starter with angular contact thrust bearing |
| US20100043444A1 (en) * | 2006-11-30 | 2010-02-25 | Rafael Advanced Defense Systems Ltd. | Starting turbine engines |
| CN102383942A (en) * | 2010-06-30 | 2012-03-21 | 通用电气公司 | System and method for fast turbine deceleration |
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| US20040234369A1 (en) * | 2003-05-19 | 2004-11-25 | Feest Robert H. | Air turbine starter with angular contact thrust bearing |
| US20100043444A1 (en) * | 2006-11-30 | 2010-02-25 | Rafael Advanced Defense Systems Ltd. | Starting turbine engines |
| CN102383942A (en) * | 2010-06-30 | 2012-03-21 | 通用电气公司 | System and method for fast turbine deceleration |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106458323A (en) * | 2014-04-03 | 2017-02-22 | 赛峰直升机发动机公司 | Drive chain for a helicopter incorporating a pyrotechnic assistance drive module and helicopter comprising same |
| CN105179087A (en) * | 2015-09-13 | 2015-12-23 | 张宗贤 | Power device with gunpowder combustion jet function |
| 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 |
| CN110062841A (en) * | 2016-11-18 | 2019-07-26 | 赛峰直升机发动机公司 | Pyrotechnic |
| US11359545B2 (en) | 2016-11-18 | 2022-06-14 | Safran Helicopter Engines | Pyrotechnic device |
| CN110062841B (en) * | 2016-11-18 | 2022-07-08 | 赛峰直升机发动机公司 | Pyrotechnic device |
| CN109306901A (en) * | 2017-07-26 | 2019-02-05 | 和谐工业有限责任公司 | Air turbine engine-starters |
| US10724444B2 (en) | 2017-07-26 | 2020-07-28 | Unison Industries, Llc | Air turbine starter |
| CN109306901B (en) * | 2017-07-26 | 2021-08-24 | 和谐工业有限责任公司 | Air turbine starter |
| 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 |
| CN110714838A (en) * | 2019-11-01 | 2020-01-21 | 北京动力机械研究所 | Turbojet engine started by gas |
| CN112576378A (en) * | 2020-12-14 | 2021-03-30 | 江西洪都航空工业集团有限责任公司 | Gas turbine engine with automatic separation starting turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102889132B (en) | 2016-09-28 |
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