CN107060893A - A kind of turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure - Google Patents
A kind of turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure Download PDFInfo
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- CN107060893A CN107060893A CN201710404015.8A CN201710404015A CN107060893A CN 107060893 A CN107060893 A CN 107060893A CN 201710404015 A CN201710404015 A CN 201710404015A CN 107060893 A CN107060893 A CN 107060893A
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- rib
- trailing edge
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Classifications
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
Abstract
Seam cooling structure is partly split the invention discloses a kind of turbine blade tail flow-disturbing with V-type rib, by partly splitting slotted wall face arrangement V-type rib structure generation augmentation of heat transfer effect, on the premise of film outlet flow is not increased, air film convection transfer rate is improved by turbulence structure and heat exchange area, enhancing partly split the convection heat transfer intensity of seam gaseous film control, so as to improve the synthesis cooling effect of blade trailing edge.Turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure, be retain the wall of blade trailing edge suction surface side in blade trailing edge pressure face cut-out wall and the separation rib at interval formed it is multiple partly split crack structure, it is reasonable in design；Cooling air-flow from go out stream seam in eject be covered in partly split on slotted wall face formed cooling air film, be effectively reduced the maximum temperature and mean temperature of suction surface, it is to avoid the suction surface high temperature ablation of turbo blade.Slotted wall face arrangement V-type rib structure is partly being split, with good heat-transfer character and processing exploitativeness.
Description
Technical field
The invention belongs to turbine blade of gas turbine cooling technology field, specifically, it is related to a kind of whirlpool with V-type rib
Impeller blade trailing edge flow-disturbing partly splits seam cooling structure.
Background technology
Trailing edge is used as one of key position that cooling is needed on turbo blade.One be due to trailing edge structural intergrity for
The aeroperformance and reliability of service life of turbo blade are most important；Two be due to the combustion gas speed of pressure face and suction surface in whirlpool
Impeller blade trailing edge position has all reached at a relatively high value, and all in turbulence state, so that trailing edge position convection intensity
It is very big., must in order to ensure that the structural intergrity of trailing edge can be interior not by high-temperature fuel gas ablative degradation during one's term of military service in engine
It must efficiently be cooled down.For advanced aero engine in-service at present, the air conditioning quantity cooled down for trailing edge has accounted for height
Pressure turbo blade always cools down the about 20-30% of gas consumption.
The cooling structure of turbine blade tail mainly has full seam cooling structure, discrete aperture cooling structure and partly splits seam cooling
Three kinds of forms of structure, wherein it is to cut a part of wall of blade trailing edge pressure face partly to split seam cooling structure, only retain suction
The wall of face side and some separation ribs, so that original full seam internal cooling structure is changed into some tangentially goes out stream seam,
Cold air ejects to be covered in partly to split from tangential seam forms cooling air film on slotted wall face, this structure only need to be to trailing edge suction surface side
Wall is cooled down.Propose to employ the trailing edge of high-pressure turbine blade two kinds of methods for cooling in United States Patent (USP) US6174135,
Relatively low root of blade region is distributed in leaf temperature and uses discrete aperture cooling structure, and is adopted in the higher vane tip of temperature
With partly splitting crack structure.Although the structure considers the structural strength problem of root of blade, and causes by using discrete aperture
The heat exchange area increase of cooling gas runner, the air conditioning quantity for taking away identical heat needs is reduced, and extends the life-span of blade, but
It is that from the perspective of turbo blade aeroperformance, under conditions of intensity permission, blade trailing edge thickness should be thin as best one can, to subtract
The Trailing Edge Loss of small turbo blade.Constrained by processing technology, discrete aperture cooling structure requires that turbine blade tail must have
Enough thickness can just be realized.And partly split seam cooling structure and there was only unilateral wall, and have the booster action of separation rib, therefore
The ratio that trailing edge can be designed is relatively thin, so that preferable aeroperformance is realized, and also research shows partly to split the cooling of seam cooling structure
Effect is also relatively preferable, therefore using seam cooling structure is partly split more than the trailing edge of advanced aero engine turbo blade, for turbine
Blade trailing edge partly split seam Film Cooling research be also in recent years high-temperature unit of aircraft engine cooling technology research in
One of focus.But with the continuous improvement of aero-engine fuel gas temperature, tradition partly splits the cooling capacity of crack structure gradually
Ground tends to the limit, and high-pressure turbine blade trailing edge ablation phenomen appears in the suction surface side of blade trailing edge, therefore development and wound often
New turbine blade tail high-efficient cooling structure, further lifting integrates cooling effect on the basis of cold air consumption is not increased, right
In the development of advanced High Performance Aeroengine be highly desirable to it is significant.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention proposes a kind of turbine blade tail flow-disturbing with V-type rib
Partly split seam cooling structure；V-type rib structure is applied to and partly splits slotted wall face, on the premise of film outlet flow is not increased, by disturbing
Flow structure improves air film convection transfer rate and heat exchange area, enhancing partly split the convection heat transfer intensity of seam gaseous film control, so that
Improve the synthesis cooling effect of blade trailing edge.
The technical solution adopted for the present invention to solve the technical problems is:Including blade trailing edge suction surface, blade trailing edge pressure
Power face, Trailing edge Slot wall, separation rib, continuous V-shaped rib, it is characterized in that in blade trailing edge pressure face cut-out wall, protecting
The wall of blade trailing edge suction surface side and the separation rib at interval is stayed to form multiple labial lamina thickness partly split crack structure, partly split crack structure
It is 0.2~1.5 to spend t to go out stream to stitch height s ratio with cold air, and it is 0~15 ° partly to split seam inclination angle, and cooling air-flow is exported from cold flow
In eject be covered on Trailing edge Slot wall formed cooling air film；The continuous V-shaped rib is equidistantly uniformly arranged in cold flow
The Trailing edge Slot wall of exit site, and be connected with two adjacent separation ribs；The high h of rib and cold air of the continuous V-shaped rib
It is 0.1~0.5 to go out stream seam height s ratios, and the rib width l and high h of rib ratio is 0.6~1.5, continuous V-shaped rib flow to spacing x with
Rib width l ratio is 6~10.
The continuous V-shaped rib is made up of two symmetrical fins, and the tilting channelization angle of fin is 30~75 °, continuous V
The opening of type rib is consistent or opposite with flow direction.
The quantity of the continuous V-shaped rib according to trailing edge split slotted wall face flow to length L, continuous V-shaped rib flow to spacing x,
The high h of rib width l, rib and channelization angle are determined.
Beneficial effect
A kind of turbine blade tail flow-disturbing with V-type rib proposed by the present invention partly splits seam cooling structure, by partly splitting
Slotted wall face arrangement V-type rib structure produces augmentation of heat transfer effect, on the premise of film outlet flow is not increased, is carried by turbulence structure
High air film convection transfer rate and heat exchange area, enhancing partly split the convection heat transfer intensity of seam gaseous film control, so as to improve blade
The synthesis cooling effect of trailing edge.Turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure, is in blade trailing edge pressure
Face cut-out wall, retain the wall of blade trailing edge suction surface side and the separation rib at interval formed it is multiple partly split crack structure,
It is reasonable in design；Cooling air-flow ejects to be covered in partly to split from cold flow outlet forms cooling air film on slotted wall face, be effectively reduced
The maximum temperature and mean temperature of suction surface, it is to avoid the suction surface high temperature ablation of turbo blade.Partly splitting, slotted wall face arrangement is simple
V-type rib structure, not only with good heat-transfer character, and with preferably processing exploitativeness, and can be applied to various whirlpools
In impeller blade.
Brief description of the drawings
Seam is partly split to a kind of turbine blade tail flow-disturbing with V-type rib of the present invention with embodiment below in conjunction with the accompanying drawings cold
But structure is described in further detail.
Fig. 1 partly splits seam cooling structure axonometric drawing for turbine blade tail flow-disturbing of the present invention with V-type rib.
Fig. 2 partly splits seam cooling structure top view for turbine blade tail flow-disturbing of the present invention with V-type rib.
Fig. 3 is Fig. 2 of the present invention A-A sectional views.
Fig. 4 partly splits seam cooling structure side view for turbine blade tail flow-disturbing of the present invention with V-type rib.
Fig. 5 is applied to aero engine turbine blades schematic diagram.
Fig. 6 is two-dimentional Trailing edge Slot heat transfer model schematic diagram.
Fig. 7 is that flow-disturbing partly splits seam cooling structure and conventional trailing edge and partly splits the exhibition for partly splitting slotted wall face of crack structure to average air film
Cooling effectiveness correlation curve.
Fig. 8 is that flow-disturbing partly splits seam cooling structure and conventional trailing edge and partly splits the exhibition for partly splitting slotted wall face of crack structure to Average heat transfer
Index contrast curve.
In figure:
1. the trailing edge of 2. separation rib of blade trailing edge pressure face 3. splits the outlet of the cold flow of 4. continuous V-shaped rib of seam surface 5.
6. the trailing edge region of 7. cold inlet of blade trailing edge suction surface 8.
Embodiment
The present embodiment is that a kind of turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure.
Refering to Fig. 1~Fig. 6, turbine blade tail flow-disturbing of the present embodiment with V-type rib partly splits seam cooling structure, is applied to
Aero engine turbine blades, the flow-disturbing partly split seam cooling structure apply in the trailing edge region 8 of turbo blade, by blade trailing edge
Suction surface 6, blade trailing edge pressure face 1, Trailing edge Slot wall 3, separation rib 2, continuous V-shaped rib 4, cold flow outlet 5, cold inlet
7 compositions；Wherein, in the cut-out wall of blade trailing edge pressure face 1, wall and the interval of the side of blade trailing edge suction surface 6 are retained
Separation rib 2 formed it is multiple partly split crack structure, it is 0.2 partly to split the ratio that the labial lamina thickness t of crack structure goes out stream seam height s with cold air
~1.5, it is 0~15 ° partly to split seam inclination angle, and cooling air-flow is ejected from cold flow outlet 5 and is covered on Trailing edge Slot wall 3
Form cooling air film.Continuous V-shaped rib 4 is equidistantly uniformly arranged Trailing edge Slot wall 3 in cold flow exit site, and with it is adjacent
Two separation ribs 2 be connected；It is 0.1~0.5 that the high h of rib of continuous V-shaped rib goes out stream seam height s ratios with cold air, and rib width l is high with rib
H ratio is 0.6~1.5, and the ratio for flowing to spacing x and rib width l of continuous V-shaped rib 4 is 6~10.Continuous V-shaped rib 4 is by two
Symmetrical fin composition, the tilting channelization angle of fin is 30~75 °, and the opening of continuous V-shaped rib is consistent or opposite with flow direction.
Flow to the length L, continuous V-shaped rib 4 that the quantity of continuous V-shaped rib 4 splits slotted wall face 3 according to trailing edge flow to spacing x, rib
The high h of wide l, rib and channelization angle are determined.
In the present embodiment, the cooling air-flow from blade interior cooling chamber enters trailing edge region 8 from cold inlet 7, from cold
Slotted wall face 3 is split along trailing edge in flow export 5 to blow out, and mixed with the high temperature main flow of blade trailing edge pressure face 1, split in corresponding trailing edge
Slotted wall face 3 forms cooling air film.Continuous V-shaped rib 4 is arranged on slotted wall face 3 by being split in trailing edge so that the cooling air film in the region
Generation flowing, separation, attached again, additions of wall turbulence structure will certainly go halves the near-wall model structure generation of seam air film jet
Influence, will also change the convection heat transfer intensity on trailing edge surface.It is that air film is cold for blade trailing edge pressure face 1 partly to split seam cooling structure
But, it is then internal cooling for blade trailing edge suction surface 6, on the one hand cold air film will completely cut off the combustion gas pair of blade trailing edge pressure face 1
The heating in trailing edge region 8, on the other hand will also absorb the heat that the combustion gas of blade trailing edge suction surface 6 is imported by trailing edge wall.It is logical
Turbulence structure is crossed to improve air film convection transfer rate and heat exchange area, strengthen the convection heat transfer intensity for partly splitting seam gaseous film control,
So as to improve the synthesis cooling effect of trailing edge.
As Fig. 7 and Fig. 8 flow-disturbing is partly split respectively seam cooling structure and conventional trailing edge partly split crack structure partly split slotted wall face
Open up and contrasted to average gas film cooling efficiency and the coefficient of heat transfer.
In the present embodiment, the turbine blade tail flow-disturbing with continuous V-shaped rib 4 is partly split in seam cooling structure, in trailing edge
Split slotted wall face 3 and arrange three row's continuous V-shaped ribs 4, the high h of rib of continuous V-shaped rib 4 is that 0.1mm, rib width l are 0.1mm, flow to spacing x
For 1.0mm, the included angle of fin is that channelization angle is 60 °, and the opening of continuous V-shaped rib 4 is consistent with flow direction.To ensure comparativity,
Both are simulated under the same conditions, and the labial lamina thickness t for partly splitting crack structure is 0.4mm, and trailing edge wall thickness δ is 1.0mm, cold flow
5 height s are exported for 0.5mm, it is 0 ° partly to split seam inclination angle, and blowing ratio M is 1.0, and difference is only that trailing edge splits whether slotted wall face 3 is arranged
Continuous V-shaped rib 4.
Contrast visible by opening up to average gas film cooling efficiency, conventional trailing edge partly splits the cooling effectiveness of crack structure than flow-disturbing half
The cooling effectiveness for splitting seam cooling structure is higher, but difference is less, and this is due to that the flow-disturbing effect of continuous V-shaped rib is caused；It is logical
The exhibition of crossing contrasts visible to average heat transfer coefficient, and the coefficient of heat transfer that flow-disturbing partly splits seam cooling structure will partly be split apparently higher than conventional trailing edge
The coefficient of heat transfer of crack structure, this mainly has benefited from the enhanced heat exchange effect brought in the continuous V-shaped rib 4 that trailing edge splits the arrangement of slotted wall face 3
Really.
The result of the average cooling effectiveness of area and convection transfer rate is as shown in the table:
| Flow-disturbing partly splits seam cooling structure | Conventional trailing edge partly splits crack structure | |
| Partly split the gas film cooling efficiency in slotted wall face | 0.98565 | 0.99667 |
| Partly split the convection transfer rate in slotted wall face | 3903.3409W/m2·k | 1998.6494W/m2·k |
| The convection transfer rate of trailing edge suction surface | 1479.387W/m2·k | 1258.793W/m2·k |
It will be appreciated from fig. 6 that it is gaseous film control for blade trailing edge pressure face 1 partly to split seam cooling structure, inhaled for blade trailing edge
Power face 6 is then internal cooling, and on the one hand cold air film will completely cut off heating of the combustion gas of blade trailing edge pressure face 1 to trailing edge region 8, separately
On the one hand the heat that the combustion gas of blade trailing edge suction surface 6 is imported by trailing edge wall is also absorbed.Therefore the side of blade trailing edge suction surface 6
Wall temperature Tw2Seam wall surface temperature T is split higher than trailing edgew1, and the synthesis cooling effect of trailing edge also just depends primarily on blade trailing edge suction
The reduction degree of the wall temperature of face 6.
Under the hypothesis of the boundary condition shown in Fig. 6 and one dimensional heat transfer process, pass through following heat transfer equilibrium equation:
In formula, TgFor fuel gas temperature, TcFor cold air temperature, t is partly splits seam labial lamina thickness, and s is cold flow outlet height, and δ is tail
Edge wall thickness, k is trailing edge wall thermal conductivity factor, hgFor the convection transfer rate of blade trailing edge suction surface, Tw2For blade trailing edge suction
Face the wall and meditate temperature, Tw1For Trailing edge Slot wall surface temperature, hfFor the convection transfer rate on Trailing edge Slot wall, η is that trailing edge is partly split
Gas film cooling efficiency on slotted wall face.
Blade trailing edge suction surface side wall temperature T can obtain by formula (1)w2Imitated with fuel gas temperature, cold air temperature, gaseous film control
Rate, and two side walls convection transfer rate relational expression:
By respective value bring into formula (2)-(3) can obtain conventional trailing edge partly split crack structure and flow-disturbing partly split seam cooling structure leaf
Piece trailing edge suction surface wall temperature is respectively 1070.958K and 974.069K, it is seen that the turbine blade tail with continuous V-shaped rib 4 is disturbed
Stream partly splits seam cooling structure, can be effectively reduced the wall temperature of blade trailing edge suction surface 6.
Claims (3)
1. a kind of turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure, including blade trailing edge suction surface, blade tail
Edge pressure face, Trailing edge Slot wall, separation rib, continuous V-shaped rib, it is characterised in that:In blade trailing edge pressure face cut-out
Wall, retain the wall of blade trailing edge suction surface side and the separation rib at interval formed it is multiple partly split crack structure, partly split crack structure
Labial lamina thickness t and cold air to go out stream seam height s ratio be 0.2~1.5, it is 0~15 ° partly to split seam inclination angle, cooling air-flow from
Eject to be covered on Trailing edge Slot wall in cold flow outlet and form cooling air film；The continuous V-shaped rib is equidistantly laid
The Trailing edge Slot wall in cold flow exit site is put, and is connected with two adjacent separation ribs；The rib of the continuous V-shaped rib is high
It is 0.1~0.5 that h goes out stream seam height s ratios with cold air, and the rib width l and high h of rib ratio is 0.6~1.5, the flow direction of continuous V-shaped rib
Spacing x and rib width l ratio is 6~10.
2. the turbine blade tail flow-disturbing according to claim 1 with V-type rib partly splits seam cooling structure, its feature exists
In:The continuous V-shaped rib is made up of two symmetrical fins, and the tilting channelization angle of fin is 30~75 °, continuous V-shaped rib
Opening it is consistent or opposite with flow direction.
3. the turbine blade tail flow-disturbing according to claim 1 with V-type rib partly splits seam cooling structure, its feature exists
In:The quantity of the continuous V-shaped rib according to trailing edge split slotted wall face flow to length L, continuous V-shaped rib flow to spacing x, rib width l,
The high h of rib and channelization angle are determined.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111502770A (en) * | 2020-04-24 | 2020-08-07 | 哈尔滨工程大学 | Cactus-imitating half-splitting-slit cooling structure suitable for high-temperature turbine blades |
| CN112282854A (en) * | 2020-09-23 | 2021-01-29 | 哈尔滨工业大学 | Turbine blade of gas turbine engine with V-shaped airflow differential plate |
| CN112343666A (en) * | 2020-12-14 | 2021-02-09 | 北京航空航天大学 | Be applied to half corrugated rib water conservancy diversion structure of splitting seam of turbine blade trailing edge |
| CN112343667A (en) * | 2020-12-14 | 2021-02-09 | 北京航空航天大学 | Continuous V-shaped rib flow guide structure applied to turbine blade trailing edge half-splitting seam |
| CN112459852A (en) * | 2020-12-14 | 2021-03-09 | 北京航空航天大学 | Be applied to two water conservancy diversion rib water conservancy diversion structures of turbine blade trailing edge half-splitting seam |
| CN112523810A (en) * | 2020-12-14 | 2021-03-19 | 北京航空航天大学 | Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam |
| CN113107608A (en) * | 2021-04-13 | 2021-07-13 | 西北工业大学 | A vortex screw hole cooling structure and turbine blade for turbine blade trailing edge |
| CN114575932A (en) * | 2022-04-02 | 2022-06-03 | 中国航发沈阳发动机研究所 | Turbine blade trailing edge half-splitting seam cooling structure |
| CN114876581A (en) * | 2022-05-12 | 2022-08-09 | 中国航发沈阳发动机研究所 | Turbine blade trailing edge enhanced heat exchange semi-split seam cooling structure |
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| CN103403299A (en) * | 2011-03-11 | 2013-11-20 | 株式会社Ihi | Turbine blade |
| CN106168143A (en) * | 2016-07-12 | 2016-11-30 | 西安交通大学 | A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket |
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| CN103403299A (en) * | 2011-03-11 | 2013-11-20 | 株式会社Ihi | Turbine blade |
| CN106168143A (en) * | 2016-07-12 | 2016-11-30 | 西安交通大学 | A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111502770A (en) * | 2020-04-24 | 2020-08-07 | 哈尔滨工程大学 | Cactus-imitating half-splitting-slit cooling structure suitable for high-temperature turbine blades |
| CN112282854A (en) * | 2020-09-23 | 2021-01-29 | 哈尔滨工业大学 | Turbine blade of gas turbine engine with V-shaped airflow differential plate |
| CN112343666A (en) * | 2020-12-14 | 2021-02-09 | 北京航空航天大学 | Be applied to half corrugated rib water conservancy diversion structure of splitting seam of turbine blade trailing edge |
| CN112343667A (en) * | 2020-12-14 | 2021-02-09 | 北京航空航天大学 | Continuous V-shaped rib flow guide structure applied to turbine blade trailing edge half-splitting seam |
| CN112459852A (en) * | 2020-12-14 | 2021-03-09 | 北京航空航天大学 | Be applied to two water conservancy diversion rib water conservancy diversion structures of turbine blade trailing edge half-splitting seam |
| CN112523810A (en) * | 2020-12-14 | 2021-03-19 | 北京航空航天大学 | Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam |
| CN112523810B (en) * | 2020-12-14 | 2021-08-20 | 北京航空航天大学 | Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam |
| CN112343666B (en) * | 2020-12-14 | 2021-08-24 | 北京航空航天大学 | Be applied to half corrugated rib water conservancy diversion structure of splitting seam of turbine blade trailing edge |
| CN112459852B (en) * | 2020-12-14 | 2021-09-24 | 北京航空航天大学 | Be applied to two water conservancy diversion rib water conservancy diversion structures of turbine blade trailing edge half-splitting seam |
| CN113107608A (en) * | 2021-04-13 | 2021-07-13 | 西北工业大学 | A vortex screw hole cooling structure and turbine blade for turbine blade trailing edge |
| CN114575932A (en) * | 2022-04-02 | 2022-06-03 | 中国航发沈阳发动机研究所 | Turbine blade trailing edge half-splitting seam cooling structure |
| CN114876581A (en) * | 2022-05-12 | 2022-08-09 | 中国航发沈阳发动机研究所 | Turbine blade trailing edge enhanced heat exchange semi-split seam cooling structure |
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Application publication date: 20170818 |