CN2098556U - Cooling blades of turbine rotor - Google Patents
Cooling blades of turbine rotor Download PDFInfo
- Publication number
- CN2098556U CN2098556U CN 91209588 CN91209588U CN2098556U CN 2098556 U CN2098556 U CN 2098556U CN 91209588 CN91209588 CN 91209588 CN 91209588 U CN91209588 U CN 91209588U CN 2098556 U CN2098556 U CN 2098556U
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- CN
- China
- Prior art keywords
- blade
- turbine rotor
- cooling chamber
- cooling
- working medium
- 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.)
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a cooling blade of a turbine rotor. Comprising a connection end and a blade body twisted at an angle on the connection end, the inner of the blade body is provided with an or a plurality of parallel enclosed cooling cavities whose inner walls are provided with liquid-sucking cores injected with an amount of medium with unequal thickness, therefore, a rotating heat pipe structure is formed in the inner part. The utility model has the advantages of good cooling effect and not aerodynamic losses.
Description
The utility model relates to a kind of turbine rotor blade, particularly a kind of turbine rotor cooled blade that is used for aeroengine.
In aeroengine, for guaranteeing turbine safe handling under high as far as possible temperature, need cool off turbine rotor blade, the cooling means of existing aeroturbine blade is to adopt the high-pressure air that extrudes from gas compressor to make freezing mixture, allow cooling air flow into the blade inner chamber from root of blade, air film hole on blade tip, blade trailing edge, leaf basin or the blade back flows out then, thereby reach the effect of cooled blade, there are the following problems for the method: one, make freezing mixture with air, the coefficient of heat transfer is little, cooling effect is poor; Two, the temperature of cooling air itself is higher, so cooling effect is poor; Three, cooling air flows into blade grid passage and brings aerodynamic loss.In order to solve one, 2 two problem, adopt the technological scheme that in cooling air, participates in a certain proportion of moisture content abroad, but this requires to load a large amount of water that cooling consumes that is used on the aircraft, obviously influence flight and carrying capacity, and this scheme can not solve the 3rd problem.
The purpose of this utility model is intended to overcome above-mentioned the deficiencies in the prior art, has proposed the turbine rotor blade that a kind of its inside has the rotating heat pipe structure, has the characteristics of good cooling results, no aerodynamic loss.
The utility model comprises a joining end that can match with wheel disk of turbine, and the top of joining end is the blade of blade root, angled distortion, has the cooling chamber of or several sealings arranged side by side in the blade; The part of cooling chamber promptly is the hot junction of cooling chamber in blade, and another part promptly is the cold junction of cooling chamber deeply to joining end; The inwall of cooling chamber from blade root to blade tip disposes the imbibition core that thickness does not wait; Be marked with an amount of cooling working medium in the cooling chamber, be the requirement of cooling working medium: under the pressure of hot junction, saturation temperature be vapourizing temperature than blade to bear limiting temperature low; Under cold junction pressure, saturation temperature be condensing temperature more than normal temperature, for example, working medium can adopt mercury, water etc., disposes blower inlet casing on the inwall of cooling chamber cold junction, flows to the imbibition core to guarantee condensed cooling working medium.
Because the centrifugal action of turbine rotor, liquid cooled working medium is moved to the blade tip direction along the imbibition core, at this moment, because the part of cooling chamber in blade is the hot junction, then liquid cooled working medium is because the high temperature heating is constantly flashed to the gaseous state cooling working medium, the gaseous state cooling working medium is forced into cold junction, be cooled and the liquid cooled working medium of congealing at cold junction, liquid cooled working medium flows to blade tip along the imbibition core again, so repeatedly, having formed liquid cooled working medium becomes steam state in hot junction evaporation heat absorption and flows to cold junction, in the cold junction condensation heat release process that circulates of liquefy again, make heat constantly be brought to cold junction, pass to the cold junction cool stream then and take away, reach the effect that blade is cooled off from the hot junction.
This shows: one, cooling procedure of the present utility model is finished by evaporation and condensation process; Two, the cooling fluid that adopts of the utility model cold junction outer wall needs not be the high pressure cooled gas of higher temperature, and as can adopting water etc., and the cold junction outer wall also can adopt the special-shaped profile that is beneficial to heat exchange, and these two characteristics make that all cooling effectiveness greatly improves; Three, cooling procedure is to circulate in cooling chamber that seals and wheel disc by cooling medium to form, and does not influence aeroperformance so there is freezing mixture to flow into the main flow field.
Fig. 1 is a distortion sectional view of the present utility model.
Fig. 2 is the P-P view.
Fig. 3 is the Q-Q view.
Fig. 4 is the G view.
With reference to accompanying drawing, the utility model comprises blade tip (1), blade (2), the blade root (3) that cooperation is integrated and the union end (4) that can match with steam turbine disk, Have the cooling chamber (5) of or several sealings arranged side by side in the blade (2), cooling chamber (5) is deeply to union end (4); (ABCD) part of cooling chamber (5) is the hot junction. (AED) part is cold junction, disposes the liquid-sucking core (6) that thickness does not wait on the inwall of hot junction (ABCD); Be marked with working medium (7) in the cooling chamber (5), dispose blower inlet casing (8) on (AED) inwall of cooling chamber (5).
Most preferred embodiment:
One, have a cooling chamber (5) in the blade (2), imbibition core (6) adopts the uneven anisotropic material of being made by nichrome of voids; Locating near blade tip (1), imbibition core (6) is thinner; Working medium (7) is mercury.
Two, have three cooling chambers (5) in the blade (2), imbibition core (6) adopts GE1541 silk die porous material.At the position near blade root (3), the voids of porous material is than the voids height at close blade tip (1) position; The aperture of porous material is littler than the aperture at close blade tip (1) position.Imbibition core (6) is more and more thinner to blade tip (1) from blade root (3), and working medium (7) is water.
Claims (9)
1, turbine rotor cooled blade, comprise a joining end that can match with wheel disk of turbine, the top of joining end is the blade and the blade tip of blade root, angled distortion, feature of the present utility model is, have the cooling chamber of or several sealings arranged side by side in the blade, the part of cooling chamber is in blade, it promptly is the hot junction of cooling chamber, another part is deeply to joining end, it promptly is the cold junction of cooling chamber, the inwall of cooling chamber from blade root to blade tip disposes the imbibition core that thickness does not wait, and is marked with cooling working medium in the cooling chamber.
According to the described turbine rotor cooled blade of claim 1, it is characterized in that 2, described imbibition core is more and more thinner to blade tip from blade root.
3, turbine rotor cooled blade according to claim 1, it is characterized in that, described cooling working medium be saturation temperature under the pressure of hot junction be vapourizing temperature than blade bear limiting temperature low and under cold junction pressure full temperature be the liquid of condensing temperature more than normal temperature.
4, turbine rotor cooled blade according to claim 2 is characterized in that, the uneven anisotropic material of voids that described imbibition core is made by nichrome is formed.
5, turbine rotor cooled blade according to claim 2 is characterized in that, described imbibition core is made up of GE1541 silk die porous material
6, turbine rotor cooled blade according to claim 3 is characterized in that, described cooling working medium is a water.
7, turbine rotor cooled blade according to claim 3 is characterized in that, described cooling working medium is a mercury.
8, turbine rotor cooled blade according to claim 5 is characterized in that, described imbibition core is near the voids at the blade root position voids height than close blade tip position, and the aperture of porous material is littler than the aperture at close blade tip position.
9, turbine rotor cooled blade according to claim 1 is characterized in that, disposes blower inlet casing on the inwall of described cooling chamber cold junction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 91209588 CN2098556U (en) | 1991-06-01 | 1991-06-01 | Cooling blades of turbine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 91209588 CN2098556U (en) | 1991-06-01 | 1991-06-01 | Cooling blades of turbine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2098556U true CN2098556U (en) | 1992-03-11 |
Family
ID=4918527
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 91209588 Withdrawn CN2098556U (en) | 1991-06-01 | 1991-06-01 | Cooling blades of turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2098556U (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1872491B (en) * | 2005-06-02 | 2010-09-01 | 通用电气公司 | Methods and systems for assembling shrouded turbine bucket and tangential entry dovetail |
| CN102168584A (en) * | 2010-02-25 | 2011-08-31 | 通用电气公司 | Turbine blade with shielded coolant supply passageway |
| CN104074556A (en) * | 2013-03-29 | 2014-10-01 | 通用电气公司 | Hot gas path component for turbine system |
| CN104121037A (en) * | 2014-07-18 | 2014-10-29 | 北京航空航天大学 | Heat pipe turbine disc |
| CN105114128A (en) * | 2015-09-07 | 2015-12-02 | 沈阳航空航天大学 | Turbine blade structure under air cooling and heat pipe heat transfer combined action |
| CN105276814A (en) * | 2015-11-04 | 2016-01-27 | 苏俊兰 | Novel dust-removal tubular efficient heating furnace |
| CN105276811A (en) * | 2015-11-04 | 2016-01-27 | 苏俊兰 | Tubular efficient heating furnace |
| CN105736145A (en) * | 2016-01-28 | 2016-07-06 | 南京航空航天大学 | Aircraft engine rectification cap anti-icing device and method adopting axial rotating heat pipe |
| CN106761950A (en) * | 2017-01-13 | 2017-05-31 | 大连理工大学 | A kind of hot plate samming is without blending turbine blade cooling device and method |
| CN106885485A (en) * | 2017-02-25 | 2017-06-23 | 长沙理工大学 | Hot end variable cross-section multi-pulsation cold end heat pipe radiator |
| CN106988787A (en) * | 2016-01-21 | 2017-07-28 | 中航商用航空发动机有限责任公司 | Rotor blade and turbomachine |
| CN109763864A (en) * | 2018-12-26 | 2019-05-17 | 苏州大学 | A kind of turbine stator vane, turbine stator vane cooling structure and cooling means |
| CN110879159A (en) * | 2019-12-27 | 2020-03-13 | 长安大学 | High-temperature high-humidity aerosol sampling device and sampling method |
-
1991
- 1991-06-01 CN CN 91209588 patent/CN2098556U/en not_active Withdrawn
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1872491B (en) * | 2005-06-02 | 2010-09-01 | 通用电气公司 | Methods and systems for assembling shrouded turbine bucket and tangential entry dovetail |
| CN102168584B (en) * | 2010-02-25 | 2015-06-17 | 通用电气公司 | Turbine blade with shielded coolant supply passageway |
| CN102168584A (en) * | 2010-02-25 | 2011-08-31 | 通用电气公司 | Turbine blade with shielded coolant supply passageway |
| CN104074556B (en) * | 2013-03-29 | 2017-09-15 | 通用电气公司 | Hot gas path part for turbine system |
| CN104074556A (en) * | 2013-03-29 | 2014-10-01 | 通用电气公司 | Hot gas path component for turbine system |
| US10100666B2 (en) | 2013-03-29 | 2018-10-16 | General Electric Company | Hot gas path component for turbine system |
| CN104121037A (en) * | 2014-07-18 | 2014-10-29 | 北京航空航天大学 | Heat pipe turbine disc |
| CN105114128A (en) * | 2015-09-07 | 2015-12-02 | 沈阳航空航天大学 | Turbine blade structure under air cooling and heat pipe heat transfer combined action |
| CN105276811A (en) * | 2015-11-04 | 2016-01-27 | 苏俊兰 | Tubular efficient heating furnace |
| CN105276814A (en) * | 2015-11-04 | 2016-01-27 | 苏俊兰 | Novel dust-removal tubular efficient heating furnace |
| CN106988787A (en) * | 2016-01-21 | 2017-07-28 | 中航商用航空发动机有限责任公司 | Rotor blade and turbomachine |
| CN106988787B (en) * | 2016-01-21 | 2019-05-21 | 中国航发商用航空发动机有限责任公司 | Rotor blade and turbomachine |
| CN105736145A (en) * | 2016-01-28 | 2016-07-06 | 南京航空航天大学 | Aircraft engine rectification cap anti-icing device and method adopting axial rotating heat pipe |
| CN106761950A (en) * | 2017-01-13 | 2017-05-31 | 大连理工大学 | A kind of hot plate samming is without blending turbine blade cooling device and method |
| CN106885485A (en) * | 2017-02-25 | 2017-06-23 | 长沙理工大学 | Hot end variable cross-section multi-pulsation cold end heat pipe radiator |
| CN109763864A (en) * | 2018-12-26 | 2019-05-17 | 苏州大学 | A kind of turbine stator vane, turbine stator vane cooling structure and cooling means |
| CN110879159A (en) * | 2019-12-27 | 2020-03-13 | 长安大学 | High-temperature high-humidity aerosol sampling device and sampling method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |