CN203685393U - Ground gas turbine changed from small aero-engine - Google Patents
Ground gas turbine changed from small aero-engine Download PDFInfo
- Publication number
- CN203685393U CN203685393U CN201320825761.1U CN201320825761U CN203685393U CN 203685393 U CN203685393 U CN 203685393U CN 201320825761 U CN201320825761 U CN 201320825761U CN 203685393 U CN203685393 U CN 203685393U
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- China
- Prior art keywords
- turbine
- gas turbine
- changed
- engine
- ground gas
- 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.)
- Expired - Lifetime
Links
- 238000010304 firing Methods 0.000 claims description 21
- 238000009413 insulation Methods 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 238000002485 combustion reaction Methods 0.000 abstract description 7
- 238000012423 maintenance Methods 0.000 abstract description 3
- 230000005540 biological transmission Effects 0.000 abstract 2
- 239000002283 diesel fuel Substances 0.000 abstract 1
- 239000003350 kerosene Substances 0.000 abstract 1
- 239000003570 air Substances 0.000 description 13
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 239000006200 vaporizer Substances 0.000 description 1
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model relates to a ground gas turbine changed from a small aero-engine. The ground gas turbine changed from the small aero-engine comprises a transmission gearbox, an intake casing, a gas compressor, a diffuser, a combustion chamber, a turbine guider, a turbine, an exhaust tube outer casing and the like, wherein the transmission gearbox is connected with the intake casing by a screw, the gas compressor is installed with the turbine in a back-to-back form, a bearing is located at a cold end, and a backflow annular combustion chamber is used as the combustion chamber, thus the structure is more compact, and the axial dimensions of the device are smaller. The ground gas turbine changed from the small aero-engine disclosed by the utility model is mainly suitable for being used by an armoured vehicle; aviation kerosene combusted by the combustion chamber is changed into light diesel oil; the ground gas turbine changed from the small aero-engine is compact in structure, few in components, high in reliability, low in maintenance cost, capable of providing a bleed air flow of 0.5 kg/s and outputting a shaft power of 30 kW due to a rated rotational speed of 61515 r/min, light in weight, small in size, and high in actual application value.
Description
Technical field
The utility model relates to a kind of small aero and changes ground gas turbine.
Background technique
The small aero of light diesel of burning changes a ground gas turbine, and its effect is to armored vehicle environmental control system supply bleed air, provides air horsepower to generator.
The structural feature that small aero changes ground gas turbine more can adapt to high motor-driven, requires that starting is fast, thermal efficiency airborne circumstance high, easy to maintenance.
What the mounted air conditioner system of prior art generally adopted use is vaporizer circularly cooling.Because automobile scenarios is severe, logistics support difficulty, along with the breakthrough of air refrigeration technology will be eliminated gradually.
Model utility content
The purpose of this utility model: provide a kind of compact structure, reliability small aero high, the light diesel that can burn to change ground gas turbine.
The technical solution of the utility model: a kind of small aero changes ground gas turbine, it is characterized in that: described small aero changes ground gas turbine and comprises uni-drive gear box 1, inlet casing 2, gas compressor 3, Diffuser 4, firing chamber 5, nozzle ring 6, turbine 7, the outer casing 8 of outlet pipe, wherein, uni-drive gear box 1 is fixed by screw with inlet casing 2, inlet casing 2 adopts footpath-axial axis symmetric mode, gas compressor 3 is connected by pull bar with turbine 6, adopt back-to-back and place, Diffuser 4 is fixed on inlet casing 2 rear ends, adopt the firing chamber 5 of backflow loop configuration to be arranged in the outer casing 8 of outlet pipe, nozzle ring 6 is arranged on firing chamber 5 and exports in the crack forming with turbine 7, turbine 7 is arranged on nozzle ring 6 rears, the outer casing 8 of outlet pipe and inlet casing 2 are by clip connected, firing chamber 5, nozzle ring 6, turbine 7 is arranged in the outer casing 8 of outlet pipe.
The beneficial effects of the utility model: the utility model adopts the symmetrical air inlet system in footpath-axial axis, have simple in structurely, lightweight, suck the features such as the danger of foreign material is little.In addition, gas compressor and turbine adopt back-to-back and place, and make product structure compacter, and bearing is all placed on cold junction, greatly increases its life-span, improve reliability.The use of backflow annular combustion chamber, is that the axial dimension of product reduces greatly, and simple in structure, is convenient to dismounting.The outer casing of inlet casing and outlet pipe adopts clip connected, makes it simple in structure, is convenient to dismounting, easy to maintenance.Ground combustion machine rated speed of the present utility model is 61515r/min, and 0.5kg/s bleed flow can be provided, and can export the air horsepower of 30kW, and the firing chamber light diesel that can burn is the key of its vehicle that can be used for installing.
This structure, also applicable to other gas turbine installations of small flow, higher pressure ratio, has certain versatility and good use value.
Brief description of the drawings:
Fig. 1 is the structural representation that small aero of the present utility model changes ground gas turbine;
Wherein, 1-uni-drive gear box, 2-inlet casing, 3-gas compressor, 4-Diffuser, 5-firing chamber, 6-nozzle ring, 7-turbine, the outer casing of 8-outlet pipe.
Embodiment
Below by embodiment, the utility model is described in further detail.
Please refer to Fig. 1, it is structural representation of the present utility model.A kind of small aero changes ground gas turbine and comprises uni-drive gear box 1, inlet casing 2, gas compressor 3, Diffuser 4, firing chamber 5, nozzle ring 6, turbine 7, the outer casing 8 of outlet pipe.Wherein, described uni-drive gear box 1 is fixed by screw with inlet casing 2, described gas compressor 3 is connected by pull bar with turbine 6, described Diffuser 4 is fixed on air inlet and supports casing rear end, it adopts radial-axial Integral design, gas is first through radially rectification compression, enter outside firing chamber 5 through axial rectification compression again, described firing chamber 5 is arranged in the outer casing 8 of outlet pipe, adopt backflow loop configuration, can make product structure simply compact, described nozzle ring 6 is placed on 5 outlet ports, firing chamber, described turbine 7 is arranged on nozzle ring 6 rears, the outer casing 8 of described outlet pipe and inlet casing are by clip connected, its inside comprises firing chamber 5, nozzle ring 6, turbine 7 high-temperature components such as grade, the outer casing 8 of outlet pipe provides bleed interface in addition, gas exhaust piping etc.
Rotor speed of the present utility model is 61515r/min, and firing chamber 5 temperature approach 1000 DEG C, and the feature of high temperature and high speed makes hot-end component work under bad environment.Gas compressor 3 adopts the cantilever structure of placing back-to-back with turbine 7, bearing is placed on air inlet and supports in casing 2, away from high-temperature components such as firing chamber 5 and turbines 7, gas compressor 3 and turbine 7 adopt intermediate seal heat insulation in addition, corresponding Diffuser 4 adopts the design of radial-axial integral type, firing chamber 5 adopts becate shape reverse flow type combustor, and guider 6 is placed on 5 outlet ports, firing chamber, and the axial dimension of device core engine shortens greatly.
Claims (2)
1. a small aero changes ground gas turbine, it is characterized in that: described small aero changes ground gas turbine and comprises uni-drive gear box (1), inlet casing (2), gas compressor (3), Diffuser (4), firing chamber (5), nozzle ring (6), turbine (7), the outer casing (8) of outlet pipe, wherein, uni-drive gear box (1) is fixed by screw with inlet casing (2), gas compressor (3) is connected by pull bar with turbine (6), Diffuser (4) is fixed on inlet casing (2) rear end, firing chamber (5) is arranged in the outer casing (8) of outlet pipe, nozzle ring (6) is arranged in the crack of firing chamber (5) outlet and turbine (7) formation, turbine (7) is arranged on nozzle ring (6) rear, the outer casing (8) of outlet pipe and inlet casing (2) are by clip connected, firing chamber (5), nozzle ring (6), turbine (7) is arranged in the outer casing (8) of outlet pipe.
2. small aero according to claim 1 changes ground gas turbine, it is characterized in that: described gas compressor (3) and turbine (7) utilize pull bar to be connected by mode back-to-back, and intermediate seal is heat insulation, and adopts cantilever structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320825761.1U CN203685393U (en) | 2013-12-12 | 2013-12-12 | Ground gas turbine changed from small aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320825761.1U CN203685393U (en) | 2013-12-12 | 2013-12-12 | Ground gas turbine changed from small aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203685393U true CN203685393U (en) | 2014-07-02 |
Family
ID=51007305
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320825761.1U Expired - Lifetime CN203685393U (en) | 2013-12-12 | 2013-12-12 | Ground gas turbine changed from small aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203685393U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114622993A (en) * | 2022-03-16 | 2022-06-14 | 湖南航翔燃气轮机有限公司 | Offset type miniature gas turbine generator set |
-
2013
- 2013-12-12 CN CN201320825761.1U patent/CN203685393U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114622993A (en) * | 2022-03-16 | 2022-06-14 | 湖南航翔燃气轮机有限公司 | Offset type miniature gas turbine generator set |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140702 |