CN202991240U - High-rotary-speed and small-size pressure control device of turbine engine - Google Patents
High-rotary-speed and small-size pressure control device of turbine engine Download PDFInfo
- Publication number
- CN202991240U CN202991240U CN 201220733616 CN201220733616U CN202991240U CN 202991240 U CN202991240 U CN 202991240U CN 201220733616 CN201220733616 CN 201220733616 CN 201220733616 U CN201220733616 U CN 201220733616U CN 202991240 U CN202991240 U CN 202991240U
- Authority
- CN
- China
- Prior art keywords
- control device
- pressure control
- rotary
- gas compressor
- small
- 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
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model belongs to the technical field of aero-engines and particularly relates to a high-rotary-speed and small-size pressure control device of a turbine engine. The high-rotary-speed and small-size pressure control device comprises a plurality of flow guide sheets 2 which are mounted in a gas compressor rotary disc cavity 1; an included angle between the flow guide sheets 2 is 60 degrees; and the flow guide sheets 2 are connected with a gas compressor disc 4 through bolts 3 and rotate along a gas compressor rotor. The pressure control device disclosed by the utility model is small in size, simple and compact in structure and low in cost, does not cause extra vibration of the engine under a high rotary speed condition, and is high in reliability. Contrast tests which use the device and not use the device at a second-grade gas entraining position of a gas compressor under an HL engine whole machine environment find that air flow pressure loss from the rot part of a blade to a disc center position is reduced by more than 20% after the pressure control device is used.
Description
Technical field
The utility model belongs to the aero engine technology field, particularly relates to the high rotating speed small size of a kind of turbogenerator pressure control device.
Background technique
Air system mainly plays in motor that high-temperature component is cooling, combustion gas and the effects such as lubricating oil is obturaged, thrust load balance, and the air system that design function is good is the basic guarantee of engine reliable work.Air system need to be from gas compressor to the turbine bleed, and the pressure control device (subtracting the whirlpool device) that is used for gas compressor bleed stream passes through the water conservancy diversion to air, and then reduce air-flow in the eddy current loss of rotation chamber flow process, reach the bleed quality that improves air system, guarantee that downstream airflow has enough pressure to be used for obturaging.At present, at home, in outer known aeroengine and gas turbine, gas compressor bleed stream pressure control device mainly contains nozzle-type, tubular type and water conservancy diversion chip, but for this small size (external diameter is 66mm approximately), it is blank that the water conservancy diversion chip air-pressure controlling device of high rotating speed (rotating speed 42000r/min) still belongs to.Therefore, the research of such pressure control device had important practical meaning in engineering.
Summary of the invention
Goal of the invention: the high rotating speed small size of a kind of size turbogenerator little, simple and compact for structure pressure control device is provided.
Technological scheme: the high rotating speed small size of a kind of turbogenerator pressure control device, comprise several guide plates 2 that are arranged in gas compressor inside rotating disc cavities 1, guide plate 2 angle each other is 60 °, and guide plate 2 is connected with compressor disc 4 by bolt 3, rotates with compressor rotor.
Guide plate 2 quantity are six.
Guide plate 2 appearance profiles are consistent with compressor disc chamber 1 shape.
Guide plate 2 is highly between 39 to 41.5mm, and width is between 29 to 31mm.
Beneficial effect: it is little that the utility model pressure control device has size, simple and compact for structure, and cost is low, can not cause the vibration that motor is extra under high speed conditions, and reliability is high.Use this device and do not use the comparative trial of this device by gas compressor secondary bleed position under HL motor complete machine environment, after finding to use this pressure control device, the stream pressure loss from root of blade to the core position can be reduced more than 20%.
Description of drawings
Fig. 1 is the utility model structural representation.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail, sees also Fig. 1.
As shown in Figure 1, the high rotating speed small size of a kind of turbogenerator pressure control device comprises several guide plates 2 that are arranged in gas compressor inside rotating disc cavities 1, and guide plate 2 angle each other is 60 °, guide plate 2 is connected with compressor disc 4 by bolt 3, rotates with compressor rotor.
Guide plate 2 quantity are six.
Guide plate 2 appearance profiles are consistent with compressor disc chamber 1 shape.
Guide plate 2 is highly between 39 to 41.5mm, and width is between 29 to 31mm.
Air is drawn from compressor blade root gap, enters gas compressor inside rotating disc cavities 1 by the vent on the gas compressor drum barrel, and then inwardly Radial Flow enters gas compressor core passage.Under the turning effort of compressor rotor up to the 42000r/min rotating speed, the air-flow that enters gas compressor inside rotating disc cavities 1 has strong eddy flow, and very easily forms free vortex flow, and this will cause very large eddy current loss, and then reduces bleed pressure.For this reason, by at gas compressor inside rotating disc cavities 1 applying pressure control gear, make the air-flow that enters gas compressor inside rotating disc cavities 1 flow along the radial passage that guide plate forms, the development of eddy current and the formation of free vortex have been controlled, the stream pressure loss be can greatly reduce, thereby bleed flow and downstream airflow pressure guaranteed.
It is little that the utility model pressure control device has size, simple and compact for structure, and cost is low, can not cause the vibration that motor is extra under high speed conditions, and reliability is high.Use this device and do not use the comparative trial of this device by gas compressor secondary bleed position under HL motor complete machine environment, after finding to use this pressure control device, the stream pressure loss from root of blade to the core position can be reduced more than 20%.
Claims (4)
1. the high rotating speed small size of a turbogenerator pressure control device, is characterized in that,
Comprise several guide plates (2) that are arranged in gas compressor inside rotating disc cavities (1), guide plate (2) angle each other is 60 °, and guide plate (2) is connected with compressor disc (4) by bolt (3), rotates with compressor rotor.
2. the high rotating speed small size of a kind of turbogenerator according to claim 1 pressure control device, is characterized in that, guide plate (2) quantity is six.
3. the high rotating speed small size of a kind of turbogenerator according to claim 2 pressure control device, is characterized in that, guide plate (2) appearance profile is consistent with compressor disc chamber (1) shape.
4. the high rotating speed small size of a kind of turbogenerator according to claim 3 pressure control device, is characterized in that, guide plate (2) is highly between 39 to 41.5mm, and width is between 29 to 31mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220733616 CN202991240U (en) | 2012-12-27 | 2012-12-27 | High-rotary-speed and small-size pressure control device of turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220733616 CN202991240U (en) | 2012-12-27 | 2012-12-27 | High-rotary-speed and small-size pressure control device of turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202991240U true CN202991240U (en) | 2013-06-12 |
Family
ID=48562428
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220733616 Expired - Lifetime CN202991240U (en) | 2012-12-27 | 2012-12-27 | High-rotary-speed and small-size pressure control device of turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202991240U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105934562A (en) * | 2013-11-26 | 2016-09-07 | 通用电气公司 | Rotor off-take assembly |
| CN110454436A (en) * | 2019-07-29 | 2019-11-15 | 中国航发沈阳发动机研究所 | A kind of short flexure type eddy plate applied to aero-engine compressor high position bleed |
| CN112161786A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Test device for vortex reducer system of rotating disc cavity |
-
2012
- 2012-12-27 CN CN 201220733616 patent/CN202991240U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105934562A (en) * | 2013-11-26 | 2016-09-07 | 通用电气公司 | Rotor off-take assembly |
| US10577966B2 (en) | 2013-11-26 | 2020-03-03 | General Electric Company | Rotor off-take assembly |
| CN105934562B (en) * | 2013-11-26 | 2020-11-17 | 通用电气公司 | Rotor bleed assembly |
| CN110454436A (en) * | 2019-07-29 | 2019-11-15 | 中国航发沈阳发动机研究所 | A kind of short flexure type eddy plate applied to aero-engine compressor high position bleed |
| CN112161786A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Test device for vortex reducer system of rotating disc cavity |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201265558Y (en) | Inlet guide blade regulator of single-axle cantilever compressor | |
| CN104675556A (en) | Large-bypass-ratio turbofan engine of vane tip jet driven fan | |
| CN104500269B (en) | With the large Bypass Ratio Turbofan Engine of self-driven fan of inner ring air turbine | |
| CN202991240U (en) | High-rotary-speed and small-size pressure control device of turbine engine | |
| CN107355314A (en) | It is segmented tandem electric rotor fanjet and its control method | |
| CN103671222A (en) | Power-driven gas compressor of novel structure | |
| CN204436597U (en) | The low loss of a kind of turbogenerator cooling system is prewhirled gas-supplying structure and turbine rotor cooling flowing path structure thereof | |
| CN103573469A (en) | Fan pneumatic layout structure and method of turbofan engine | |
| CN205277926U (en) | Intermediary's machine casket extension board and high pressure compressor import guide blade fuse structure | |
| CN103410762B (en) | A kind of centrifugal blower rotating stall control device and method | |
| CN202991148U (en) | Nozzle ring of pressurizer | |
| CN203906117U (en) | Turbofan engine with fan speed reduction and direction changing functions | |
| CN203051237U (en) | Surge-preventing structure for aero-engine compressor | |
| CN203742673U (en) | Centripetal turbine | |
| CN202665445U (en) | Anti-backflow impeller for dust collector | |
| CN215057760U (en) | Multi-rotor micro gas turbine | |
| CN205064122U (en) | Aviation air injection motor | |
| CN203809056U (en) | Centrifugal turbine | |
| CN203348128U (en) | Centrifugal fan rotating stall control device | |
| CN204402584U (en) | Nozzle ring capable of changing cross sections is carried out to the heat filter structure of pretension | |
| CN207776909U (en) | A kind of turbine that assembly precision is high | |
| CN101624945B (en) | Jet pressing burning splitting ring curled turbine engine | |
| CN204783815U (en) | Spiral aviation gas turbine engine turbine | |
| CN203847174U (en) | Stator steam inlet structure of radial-flow turbine | |
| CN103727071A (en) | Variable pressure expander of pressurizer gas compressor |
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 operation monitoring department, Jiangyou 305 mailbox, Mianyang City, Sichuan Province Patentee before: CHINA GAS TURBINE EST |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130612 |