CN102678189A - Turbine cooling blade with blade tip leakage prevention structure - Google Patents
Turbine cooling blade with blade tip leakage prevention structure Download PDFInfo
- Publication number
- CN102678189A CN102678189A CN2011104147073A CN201110414707A CN102678189A CN 102678189 A CN102678189 A CN 102678189A CN 2011104147073 A CN2011104147073 A CN 2011104147073A CN 201110414707 A CN201110414707 A CN 201110414707A CN 102678189 A CN102678189 A CN 102678189A
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- Prior art keywords
- blade
- leaf top
- leaf
- rib
- turbine
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- 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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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
Abstract
The invention relates to a turbine cooling blade with a blade tip leakage prevention structure. A blade body is internally provided with a cooling channel; a blade tip partition rib extending from the front edge of the blade body to the tail edge of the blade body is arranged on the outer surface of a blade tip plate of the blade body; and more than one jet hole communicated with the cooling channel is distributed on the blade tip plate from the front edge to the tail edge of the blade body and is positioned at one side or two sides of the blade tip partition rib along the extending direction of the blade tip partition rib. According to the turbine cooling blade with the blade tip leakage prevention structure, the blade tip partition rib is arranged on the outer surface of the blade tip plate from the front edge to the tail edge of the blade body; when in use, the blade tip partition rib is positioned in a gap between the turbine blade and the sealing structure so as to replace the existing blade tip girdle structure, so that gas loss in the blade tip gap can be reduced, and no blade tip girdle structure is needed; and at the same time, the structure of the blade tip partition rib is simple, so that the blade tip partition rib can be rapidly maintained when being abraded or damaged after long time work of the turbine blade; and therefore, the turbine blade has high maintainability.
Description
Technical field
The present invention relates to a kind of turbine cooling blade that is used on the gas turbine with leaf top leakage-proof structure.
Background technique
Turbine blade is the vitals of gas turbine; Existing turbine blade comprises blade body; The inside of blade body has the cooling channel, and at work, the leaf top top board of gas-turbine blade and casing seal structure cooperate; It is the main factor of turbine efficiency loss that the high-temperature fuel gas that gap between the two causes leaks; This is because high temperature, high pressure and the high-revolving rugged environment of turbine blade work cause the turbine disk, blade and casing because the distortion of generations such as centrifugal force, temperature stress is difficult to realize the best fit design under each operating mode, always has certain interval between turbine blade and the seal structure; And the leakage of high-temperature fuel gas can be caused in this gap, causes the loss in efficiency of turbine.Therefore, it is one of focus of gas turbine design that the blade tip clearance that how to reduce turbine to greatest extent leaks.At present, leaf roof construction commonly used is on the top board of leaf top, to increase the shroud structure with certain thickness and height of arranging along blade outer surface, forms leaf top groove structure, compares with the flat-top blade and can reduce blade tip clearance combustion gas loss largely.
When work; Leaf top top board is bearing from the scouring force of pressure side to the swiftly flowing high-temperature fuel gas of suction surface always; Therefore, need cool off, just in the cooling channel of turbine blade, cooled gas is set turbine blade; And the leaf roof construction of common cooled blade mainly relies on the transmission of heat of cooled gas in the cooling channel to realize cooling, and cooling effect is not good.The inlet gas temperature of present advanced gas turbine turbine has reached more than the 2000K, and the highest tolerable temperature of existing high-temperature alloy material is much smaller than turbine inlet temperature (TIT), and the setting of shroud structure has then further worsened the working environment on leaf top.Leaf top girth band structure often because the continuous erosion of high-temperature fuel gas produces oxide etch or spalling phenomenon, causes the increase gradually of turbine blade blade tip clearance, thereby causes high-pressure turbine working efficient to reduce even inefficacy; The Security of serious threat gas turbine operation needs regularly turbine blade to be repaired or replaced, and is of a high price; In addition; The complex structure of leaf top girth band structure, inconvenient maintenance, service cycle is longer.
Summary of the invention
The object of the present invention is to provide a kind of turbine cooling blade with leaf top leakage-proof structure; When reducing the turbine blade blade tip clearance to solve available technology adopting leaf top girth band structure, the problem that the inconvenient maintenance that causes because of the complex structure of leaf top girth band structure, service cycle are long.
For realizing above-mentioned purpose; The present invention adopts following technological scheme: a kind of turbine cooling blade with leaf top leakage-proof structure; Comprise blade body; Has the cooling channel in the blade body; The outer surface of the leaf top top board of blade body is provided with the separated rib in leaf top that is extended to trailing edge by the leading edge of blade body, and leading edge to the trailing edge by blade body on the top board of leaf top is laid with the more than one jet hole that is communicated with the cooling channel, and jet hole is laid in the one or both sides of leaf top at a distance from rib along the leaf top at a distance from the bearing of trend of rib.
Extend at a distance from the center of rib top board along leaf top camber line on said leaf top.
Described leaf top tilts towards pressure side at a distance from rib.
Described leaf top is wholely set on the top board of leaf top at a distance from rib, and described leaf top is provided with the arc-shaped transition structure at a distance from the joint of rib and leaf top top board.
Said jet hole is laid in the both sides of leaf top at a distance from rib.
Described jet hole is the inclined hole that has angle with leaf top top board.
Leading edge to trailing edge by blade body on the described pressure side is laid with the more than one air film hole that is communicated with the cooling channel.
The hole wall near leaf top top board of described air film hole partly has the drainage face that steering flow flows to the top that is used for of oblique leaf top top board.
Described air film hole is circular port or slotted eye.
Be provided with in the described cooling channel cooling channel is divided into by the leading edge of the blade body dividing plate to the back-shaped coolant flow channel of trailing edge, have the exhaust seam that more than one and back-shaped coolant flow channel is communicated with on the trailing edge of blade body.
The outer surface of leaf of the present invention top top board is provided with the separated rib in leaf top that is extended to trailing edge by leading edge; In use; The leaf top is in the gap between turbine blade and the seal structure at a distance from rib, can replace leaf top girth band structure of the prior art, plays the effect that reduces blade tip clearance combustion gas loss; Leaf top girth band structure need be set, promptly can reach the purpose that improves turbine efficiency.In addition, the leaf top is simple in structure at a distance from rib, is convenient to machine shaping; Help reducing the cost of turbine blade, in addition, compare with the leaf top girth band structure of bilateral groove structure; The leaf top has reduced the total quality of turbine blade at a distance from the lighter weight of rib, can reduce the centrifugal force of turbine blade.Simultaneously,, the leaf top after turbine blade work a period of time, occurs when rib wearing and tearing or damage, also can keep in repair fast because leaf pushes up the simple in structure of separated rib, the maintenance height of turbine blade, service cycle is longer, and cost is low.
Jet hole of the present invention is the inclined hole that has angle with leaf top top board; The setting of inclined hole not only has tangible cooling effect to leaf top top board and leaf top at a distance from rib; And also can rise warm gas leakage generation inhibition to a certain extent to leaf, and reduce the blade tip clearance loss, improve turbine efficiency.
The present invention partly has the drainage face that steering flow flows to the top that is used on oblique leaf top near the air film hole hole wall on leaf top; Drainage face makes that better to press close to the blade wall by the cooled gas that flows out in the air film hole mobile with the leaf roof construction, has improved gas film cooling efficiency.
Description of drawings
The structural representation of Fig. 1 embodiment of the invention 1;
Fig. 2 is the sectional drawing at A-A place among Fig. 1;
Fig. 3 is the partial enlarged drawing of air film hole among Fig. 1;
Fig. 4 is the structural representation of the embodiment of the invention 2.
Embodiment
A kind of embodiment 1 with turbine cooling blade of leaf top leakage-proof structure; In Fig. 1 ~ 3; Comprise blade body; Have cooling channel 20 in the blade body, cooling channel 20 encloses with trailing edge by the pressure side of blade body 21 and suction surface 22 and with the leading edge 47 that the two ends of pressure side 21 and suction surface 22 link together and forms.The top of blade body has the leaf top top board that cooling channel 20 is sealed up; The one-body molded leaf top that is provided with is at a distance from rib 24 on the outer side surface of leaf top top board; The separated rib 24 in leaf top extends to trailing edge by the leading edge 47 of blade body, and the leaf top is in camber line place, center top board along the leaf top of leaf top top board at a distance from rib 24 center camber line extends.The leaf top is obliquely installed on the top board of leaf top at a distance from rib 24, and the leaf top is at a distance from rib 24 oblique pressure sides 21.Separated rib 24 in leaf top and leaf top top board are provided with the arc-shaped transition structure near the joint of pressure side 21 sides, and the arc-shaped transition structure can be avoided the leaf top stress between rib 24 and leaf top top board, to occur and concentrate raising join strength between the two.
Be laid with jet hole 27 on the top board of leaf top, jet hole 27 is arranged in the zone of leaf top top board by leading edge 47 to the trailing edge of blade body, and the inner of jet hole 27 is communicated with cooling channel 20, and the outer end of jet hole 27 is in communication with the outside.Bearing of trend at a distance from rib 24 distributes jet hole 27 along the leaf top, and is distributed in the side of leaf top at a distance from rib 24.
Improvement as technique scheme; On pressure side 21, be laid with more than one air film hole 26; Air film hole 26 is laid on the pressure side 21 in the scope by leading edge 47 to the trailing edge of blade body, and the inner of air film hole 26 is communicated with cooling channel 20, and the outer end of air film hole 26 is in communication with the outside.
Improvement as technique scheme; Air film hole 26 is circular circular port for cross section; The hole wall near leaf top top board of air film hole 26 partly has the drainage face of oblique leaf top top board, and drainage face is used for guiding the air-flow that is flowed out by air film hole 26 to make the air flow direction top.
Improvement as the foregoing description; Be provided with in the cooling channel 20 cooling channel 20 is divided into by the leading edge 47 of the blade body dividing plate 61 to the back-shaped coolant flow channel of trailing edge; Has the exhaust seam 46 that is communicated with back-shaped coolant flow channel on the trailing edge of blade body; Exhaust seam 46 is more than one, is laid on the trailing edge of blade body.
Only be provided with the arc-shaped transition structure at a distance from rib 24 and leaf top top board near the joint of pressure side 21 sides in the present embodiment, also can with the both sides that leaf top top board is connected the arc-shaped transition structure be set all at a distance from rib 24 on the leaf top on leaf top.
A kind of embodiment 2 with turbine cooling blade of leaf top leakage-proof structure, in Fig. 4, present embodiment and embodiment's 1 difference is: jet hole 30 for and leaf top top board between have certain included angle inclined hole.And jet hole 30 is distributed in the side of leaf top at a distance from rib 24
The inner cooling channel 20 of turbine blade is divided into a plurality of back-shaped coolant flow channels by some at a distance from dividing plate 61; Cooled gas in the back-shaped coolant flow channel is flowed to leaf top top board direction by the blade root position under the guiding of dividing plate 61; Most of cooled gas is after flowing near the top board of leaf top; Or mobile through half-turn to blade root, form cooling circuit, after 90 ° of turnings are stitched 46 outflows from the trailing edge exhaust; The sub-fraction cooled gas is because air film hole 26 flows out, and after the impact that receives the main flow high-temperature fuel gas, this part cooled gas is close to pressure side 21 and is flowed along blade radial, and pressure side 21 and leaf top top board are cooled off; Another fraction cooled gas flows out from jet hole.The mainstream channel high-temperature fuel gas is when flowing through leaf top top board near zone; Part high-temperature fuel gas can directly directly flow out from the blade tip clearance 29 between rib and casing 25; This part high-temperature fuel gas can meet with the cooled gas that is flowed out by jet hole in zone, leaf top; Receive the cooled gas and the leaf that are flowed out by jet hole and push up stopping jointly of separated rib 24, this part high-temperature fuel gas forms eddy current on the leaf top at a distance from pressure side 21 sides of rib 24.The cooled gas that is flowed out by jet hole has played inhibition to the leaf top leakage of high-temperature fuel gas, and alleviates the thermal shock that the leaf top is received at a distance from rib 24.The high-temperature fuel gas of revealing from blade tip clearance 29 forms secondary flow and forms eddy current on the leaf top at a distance from rib 24 backs near suction surface 22 sides.
The cooled gas that is flowed out by jet hole effectively cools off at a distance from rib 24 leading edge 47 of turbine blade, the outer surface 23 and the leaf top of leaf top top board with the cooled gas that is flowed out by air film hole 26.
As stated; Jet hole of the present invention, the high-temperature fuel gas that can reduce blade tip clearance 29 leaks, and can effectively cool off the outer surface 23 of leaf top top board; Under the prerequisite that does not increase cooling air delivery, improve the cooling effectiveness of cooled gas; Improve the turbine inlet fuel gas temperature, thereby improve the performance and the working efficiency of gas turbine, improve the overall performance of gas turbine.
Claims (10)
1. turbine cooling blade with leaf top leakage-proof structure; Comprise blade body; Has the cooling channel in the blade body; It is characterized in that: the outer surface of the leaf top top board of blade body is provided with the separated rib in leaf top that is extended to trailing edge by the leading edge of blade body, and leading edge to the trailing edge by blade body on the top board of leaf top is laid with the more than one jet hole that is communicated with the cooling channel, and jet hole is laid in the one or both sides of leaf top at a distance from rib along the leaf top at a distance from the bearing of trend of rib.
2. the turbine cooling blade with leaf top leakage-proof structure according to claim 1 is characterized in that: extend at a distance from the center of rib top board along leaf top camber line on said leaf top.
3. the turbine cooling blade with leaf top leakage-proof structure according to claim 2 is characterized in that: described leaf top tilts towards pressure side at a distance from rib.
4. the turbine cooling blade with leaf top leakage-proof structure according to claim 3 is characterized in that: described leaf top is wholely set on the top board of leaf top at a distance from rib, and described leaf top is provided with the arc-shaped transition structure at a distance from the joint of rib and leaf top top board.
5. according to each described turbine cooling blade with leaf top leakage-proof structure in the claim 1 ~ 4, it is characterized in that: said jet hole is laid in the both sides of leaf top at a distance from rib.
6. the turbine cooling blade with leaf top leakage-proof structure according to claim 5 is characterized in that: described jet hole is the inclined hole that has angle with leaf top top board.
7. the turbine cooling blade with leaf top leakage-proof structure according to claim 1 is characterized in that: leading edge to the trailing edge by blade body on the described pressure side is laid with the more than one air film hole that is communicated with the cooling channel.
8. the turbine cooling blade with leaf top leakage-proof structure according to claim 7 is characterized in that: the hole wall near leaf top top board of described air film hole partly has the drainage face that steering flow flows to the top that is used for of oblique leaf top top board.
9. the turbine cooling blade with leaf top leakage-proof structure according to claim 8 is characterized in that: described air film hole is circular port or slotted eye.
10. the turbine cooling blade with leaf top leakage-proof structure according to claim 1; It is characterized in that: be provided with in the described cooling channel cooling channel is divided into by the leading edge of the blade body dividing plate to the back-shaped coolant flow channel of trailing edge, have the exhaust seam that more than one and back-shaped coolant flow channel is communicated with on the trailing edge of blade body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104147073A CN102678189A (en) | 2011-12-13 | 2011-12-13 | Turbine cooling blade with blade tip leakage prevention structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104147073A CN102678189A (en) | 2011-12-13 | 2011-12-13 | Turbine cooling blade with blade tip leakage prevention structure |
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| CN102678189A true CN102678189A (en) | 2012-09-19 |
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| CN2011104147073A Pending CN102678189A (en) | 2011-12-13 | 2011-12-13 | Turbine cooling blade with blade tip leakage prevention structure |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102943694A (en) * | 2012-12-05 | 2013-02-27 | 沈阳航空航天大学 | Clapboard-type labyrinth structure for moving blade tip |
| CN103422912A (en) * | 2013-08-29 | 2013-12-04 | 哈尔滨工程大学 | Turbine with moving blades with pits at blade tops |
| CN103806953A (en) * | 2014-01-20 | 2014-05-21 | 北京航空航天大学 | Novel air film holes with inclination angles |
| CN105041479A (en) * | 2015-09-09 | 2015-11-11 | 南京航空航天大学 | Aero-engine labyrinth seal structure with tooth cavity jet |
| CN104989529B (en) * | 2015-06-02 | 2016-08-17 | 哈尔滨工业大学 | Control the closed loop bleed fluidic system of turbine cascade top petiolarea flowing |
| CN106704261A (en) * | 2016-12-07 | 2017-05-24 | 浙江理工大学 | Axial flow fan ternary impeller with vein-shaped structure and nonuniform empennage |
| CN110043328A (en) * | 2018-12-17 | 2019-07-23 | 中国航发沈阳发动机研究所 | A kind of cooled change geometry low-pressure turbine guide vane |
| CN110566283A (en) * | 2019-10-09 | 2019-12-13 | 西北工业大学 | Air film cooling structure for top of high-pressure turbine power blade |
| US10619484B2 (en) | 2015-01-22 | 2020-04-14 | General Electric Company | Turbine bucket cooling |
| US10626727B2 (en) | 2015-01-22 | 2020-04-21 | General Electric Company | Turbine bucket for control of wheelspace purge air |
| US10815808B2 (en) | 2015-01-22 | 2020-10-27 | General Electric Company | Turbine bucket cooling |
| CN112240228A (en) * | 2020-10-20 | 2021-01-19 | 西北工业大学 | Discontinuous groove blade top structure for turbine blade with transverse seam hole |
| CN112523813A (en) * | 2019-09-19 | 2021-03-19 | 中国航发商用航空发动机有限责任公司 | Aeroengine turbine rim sealing structure |
| CN115341959A (en) * | 2022-07-26 | 2022-11-15 | 南京航空航天大学 | Combined blade |
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| CN202417609U (en) * | 2011-12-13 | 2012-09-05 | 河南科技大学 | Turbine cooling blade with blade tip leakage prevention structure |
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| US6059530A (en) * | 1998-12-21 | 2000-05-09 | General Electric Company | Twin rib turbine blade |
| CN1364975A (en) * | 2001-01-09 | 2002-08-21 | 通用电气公司 | Method and device for reducing the temperature of turbine leaf opex |
| US20030223870A1 (en) * | 2002-05-31 | 2003-12-04 | Keith Sean Robert | Method and apparatus for reducing turbine blade tip region temperatures |
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| EP1911934A1 (en) * | 2006-10-13 | 2008-04-16 | Snecma | Mobile blade of a turbomachine |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102943694A (en) * | 2012-12-05 | 2013-02-27 | 沈阳航空航天大学 | Clapboard-type labyrinth structure for moving blade tip |
| CN103422912A (en) * | 2013-08-29 | 2013-12-04 | 哈尔滨工程大学 | Turbine with moving blades with pits at blade tops |
| CN103422912B (en) * | 2013-08-29 | 2015-04-08 | 哈尔滨工程大学 | Turbine with moving blades with pits at blade tops |
| CN103806953A (en) * | 2014-01-20 | 2014-05-21 | 北京航空航天大学 | Novel air film holes with inclination angles |
| US10619484B2 (en) | 2015-01-22 | 2020-04-14 | General Electric Company | Turbine bucket cooling |
| US10626727B2 (en) | 2015-01-22 | 2020-04-21 | General Electric Company | Turbine bucket for control of wheelspace purge air |
| US10815808B2 (en) | 2015-01-22 | 2020-10-27 | General Electric Company | Turbine bucket cooling |
| CN104989529B (en) * | 2015-06-02 | 2016-08-17 | 哈尔滨工业大学 | Control the closed loop bleed fluidic system of turbine cascade top petiolarea flowing |
| CN105041479A (en) * | 2015-09-09 | 2015-11-11 | 南京航空航天大学 | Aero-engine labyrinth seal structure with tooth cavity jet |
| CN106704261A (en) * | 2016-12-07 | 2017-05-24 | 浙江理工大学 | Axial flow fan ternary impeller with vein-shaped structure and nonuniform empennage |
| CN106704261B (en) * | 2016-12-07 | 2023-08-18 | 杭州宏德智能装备科技有限公司 | Axial flow fan ternary impeller with vein structure and non-uniform tail fin |
| CN110043328A (en) * | 2018-12-17 | 2019-07-23 | 中国航发沈阳发动机研究所 | A kind of cooled change geometry low-pressure turbine guide vane |
| CN112523813B (en) * | 2019-09-19 | 2022-09-16 | 中国航发商用航空发动机有限责任公司 | Aeroengine turbine rim sealing structure |
| CN112523813A (en) * | 2019-09-19 | 2021-03-19 | 中国航发商用航空发动机有限责任公司 | Aeroengine turbine rim sealing structure |
| CN110566283A (en) * | 2019-10-09 | 2019-12-13 | 西北工业大学 | Air film cooling structure for top of high-pressure turbine power blade |
| CN112240228A (en) * | 2020-10-20 | 2021-01-19 | 西北工业大学 | Discontinuous groove blade top structure for turbine blade with transverse seam hole |
| CN115341959A (en) * | 2022-07-26 | 2022-11-15 | 南京航空航天大学 | Combined blade |
| CN115341959B (en) * | 2022-07-26 | 2023-07-21 | 南京航空航天大学 | Combined blade |
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Application publication date: 20120919 |