CN207829957U - Blade tip groove air film hole cooling structure - Google Patents
Blade tip groove air film hole cooling structure Download PDFInfo
- Publication number
- CN207829957U CN207829957U CN201721743030.7U CN201721743030U CN207829957U CN 207829957 U CN207829957 U CN 207829957U CN 201721743030 U CN201721743030 U CN 201721743030U CN 207829957 U CN207829957 U CN 207829957U
- Authority
- CN
- China
- Prior art keywords
- blade tip
- air film
- film hole
- tip groove
- groove
- 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.)
- Active
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model provides a kind of blade tip groove air film hole cooling structure, for aero engine turbine blades, the blade tip of the aero engine turbine blades is disposed with several air film holes, the outlet of each air film hole is provided with expanding blade tip groove, the blade tip groove includes two sides, front face and bottom surface, and described two sides symmetrically expand outwardly；The depth of the outlet initiating terminal of the air film hole is δ 1, and the wall thickness of the blade tip is δ, wherein 1≤2/3 δ of δ；Depth at the blade tip recess outlet is δ 2, wherein δ 2>0.Expanding groove structure is arranged in blade tip air film hole exits in the utility model blade tip groove air film hole cooling structure, cold air is after air film hole ejection, cold air can be dynamic close to groove wall flow along jet direction in groove, to reduce the normal velocity component of jet stream so that air film can be attached to the downstream groove surfaces of air film hole exits well.
Description
Technical field
The utility model is related to aero-engine field, more particularly to a kind of blade tip groove air film hole cooling structure.
Background technology
In aero-engine field, in order to obtain the better thermal efficiency, the fuel gas temperature before aero-turbine needs
It is continuously improved.This allows for turbo blade and is faced with increasingly severe working environment.Especially for High Pressure Turbine Rotor leaf
Piece continues high speed rotation under high temperature and high pressure environment.In order to ensure the safe and reliable work of turbine, in addition to continuing to develop new material
Other than new process, it is necessary to take efficient cooling provision to turbo blade.
Common turbine rotor blade mostly uses internal serpentine channel and turbulent flow reinforced device, and external gaseous film control is answered
Close cooling structure form.But many cooling structures are mostly to be arranged in blade position, it is seldom for rotor blade tip region
There is more effective cooling structure form.
Fig. 1 is the schematic diagram of conventional blade tip gaseous film control structure.Fig. 2 is the vertical view of conventional blade tip gaseous film control structure.
Fig. 3 is the sectional view splitted along line D-D in Fig. 2.As shown in Figure 1 to Figure 3, common turbine rotor blade tip region at present
It is cooling, it is that air film hole 11 is disposed at blade tip position 10 in blade pressure surface mostly.Exist very in blade tip region
Strong Three-dimensional Flow, cold air occur violent blending with combustion gas after air film hole ejection and act on so that cold air is difficult to attach wall surface
Flowing, 12 region cooling effect of blade tip are bad.
As described above, those skilled in the art be directed to common blade tip air film hole cooling structure, it would be highly desirable in propose corrective measure,
To enhance blade tip cooling effect.
Utility model content
The technical problems to be solved in the utility model is to overcome the cold of blade tip air film hole cooling structure in the prior art
The defects of ineffective, provides a kind of blade tip groove air film hole cooling structure.
The utility model is to solve above-mentioned technical problem by following technical proposals：
A kind of blade tip groove air film hole cooling structure is used for aero engine turbine blades, and feature is, the aviation
The blade tip of engine turbine blade is disposed with several air film holes, and it is recessed that the outlet of each air film hole is provided with expanding blade tip
Slot, the blade tip groove include two sides, front face and bottom surface, and described two sides symmetrically expand outwardly；
The depth of the outlet initiating terminal of the air film hole is δ 1, and the wall thickness of the blade tip is δ, wherein 1≤2/3 δ of δ；It is described
Depth at blade tip recess outlet is δ 2, wherein δ 2>0.
One embodiment according to the present utility model, two sides of the blade tip groove are justified with the outlet of the air film hole
Arc is tangent, and the value range of two sides of the blade tip groove and the centerlines of the air film hole is 10 ° -30 °.
The value range of one embodiment according to the present utility model, the radial angle of the air film hole is 20 ° -90 °, institute
The value range for stating the axial angle of air film hole is 20 ° -90 °.
One embodiment according to the present utility model, the bottom surface of the blade tip groove and the center line of the air film hole are formed
Angle be less than or equal to the air film hole radial angle.
One embodiment according to the present utility model, the bottom surface of the blade tip groove and the center line of the air film hole are formed
Angle value range be 5 ° -25 °.
The front face of one embodiment according to the present utility model, the blade tip groove is an arc surface.
The front face of one embodiment according to the present utility model, the blade tip groove is a flat surface, the front face
Width is more than or equal to the diameter of the air film hole.
One embodiment according to the present utility model, the front face of the blade tip groove the outlet of the air film hole most
It is tangent with the outlet profile of the air film hole at lower end position.
One embodiment according to the present utility model, the angle that the front face of the blade tip groove is formed with blade wall surface are
90°。
The exit depth δ 2 of one embodiment according to the present utility model, the blade tip groove is equal to the air film hole
Export initiating terminal depth δ 1.
The positive effect of the utility model is：
Expanding groove structure is arranged in blade tip air film hole exits in the utility model blade tip groove air film hole cooling structure, cold
Gas is after air film hole ejection, and cold air can be dynamic close to groove wall flow along jet direction in groove, to reduce jet stream
Normal velocity component so that air film can be attached to the downstream groove surfaces of air film hole exits well.In addition, air film hole rearward recess
Interior cold air can be opened up to both sides to flowing, and which enhance the exhibitions of air film to covering.By above-mentioned 2 points of collective effect, greatly improve
Gas film cooling efficiency, reduces blade tip temperature.
Description of the drawings
The above and other feature of the utility model, property and advantage will be by with reference to the accompanying drawings and examples
It describing and becomes apparent, identical reference numeral always shows identical feature in the accompanying drawings, wherein：
Fig. 1 is the schematic diagram of conventional blade tip gaseous film control structure.
Fig. 2 is the vertical view of conventional blade tip gaseous film control structure.
Fig. 3 is the sectional view splitted along line D-D in Fig. 2.
Fig. 4 is the schematic diagram of the embodiment one of the utility model blade tip groove gaseous film control structure.
Fig. 5 is the enlarged drawing of part A in Fig. 4.
Fig. 6 is the vertical view of the embodiment one of the utility model blade tip groove gaseous film control structure.
Fig. 7 is the sectional view splitted along line B-B in Fig. 5.
Fig. 8 is the scale diagrams of the embodiment one of the utility model blade tip groove gaseous film control structure.
Fig. 9 is the inclination angle schematic diagram of the embodiment one of the utility model blade tip groove gaseous film control structure.
Figure 10 is the schematic diagram of the embodiment two of the utility model blade tip groove gaseous film control structure.
Figure 11 is the enlarged drawing of the parts E in Figure 10.
Figure 12 is the vertical view of the embodiment two of the utility model blade tip groove gaseous film control structure.
Figure 13 is the sectional view splitted along line C-C in Figure 12.
Figure 14 is the scale diagrams of the embodiment two of the utility model blade tip groove gaseous film control structure.
Figure 15 is the inclination angle schematic diagram of the embodiment two of the utility model blade tip groove gaseous film control structure.
Specific implementation mode
For the above objects, features, and advantages of the utility model can be clearer and more comprehensible, below in conjunction with attached drawing to this practicality
Novel specific implementation mode elaborates.
The embodiments of the present invention are described with detailed reference to attached drawing now.Now with detailed reference to the excellent of the utility model
Embodiment is selected, its example is shown in the drawings.In the case of any possible, will be come in all the appended drawings using identical label
Indicate same or analogous part.
In addition, although the term used in the utility model is selected from public term, this reality
May be that applicant judges that detailed meanings exist come selection by his or her with some terms mentioned in novel specification
Illustrate in the relevant portion of description herein.
In addition, it is desirable that not only by used actual terms, and be also to the meaning contained by each term
To understand the utility model.
Embodiment one：
Fig. 4 is the schematic diagram of the embodiment one of the utility model blade tip groove gaseous film control structure.Fig. 5 is part A in Fig. 4
Enlarged drawing.Fig. 6 is the vertical view of the embodiment one of the utility model blade tip groove gaseous film control structure.Fig. 7 is in Fig. 5 along B-
The sectional view that B lines are splitted.Fig. 8 is the scale diagrams of the embodiment one of the utility model blade tip groove gaseous film control structure.Fig. 9
For the inclination angle schematic diagram of the embodiment one of the utility model blade tip groove gaseous film control structure.
As shown in Fig. 4 to Fig. 9, the utility model discloses a kind of blade tip groove air film hole cooling structures, are sent out for aviation
Motivation turbo blade.The blade tip 20 of the aero engine turbine blades is disposed with several air film holes 21, each air film hole 21
Outlet is provided with expanding blade tip groove 22.Wherein, blade tip groove 22 includes two sides 221, front face 222 and bottom surface 223,
Two sides 221 herein symmetrically expand outwardly.The depth of the outlet initiating terminal of air film hole 21 is δ 1, and the wall thickness of blade tip 20 is
δ, wherein 1≤2/3 δ of δ；The depth in 22 exit of blade tip groove is δ 2, and the value of δ 2 is determined by δ 1 and θ, wherein δ 2>0.
Preferably, the front face 222 of blade tip groove 22 is set as an arc surface in the present embodiment, and does not have reeded air film
Hole internal face is consistent.Two sides 221 of blade tip groove 22 and the outlet circular arc of air film hole 21 are tangent, and the two of blade tip groove 22
A side 221 and the value range of the centerlines γ of air film hole 21 are preferably 10 ° -30 °.The radial angle α of air film hole 21
Value range be preferably 20 ° -90 °, the value range of the axial angle β of air film hole 21 is preferably 0 ° -90 °.In the present embodiment
The axial angle β of air film hole 21 is set as 90 °.
Further, the angle theta that the center line of the bottom surface 223 of blade tip groove 22 and air film hole 21 is formed is less than or equal to air film
The radial angle α in hole 21.Herein, the value model for the angle theta that the center line of the bottom surface 223 of blade tip groove 22 and air film hole 21 is formed
Enclose preferably 5 ° -25 °.
In conclusion the utility model blade tip groove air film hole cooling structure is recessed in blade tip air film hole exits setting expanding
Slot structure, cold air is after air film hole ejection, and cold air can be dynamic close to groove wall flow along jet direction in groove, to reduce
The normal velocity component of jet stream so that air film can be attached to the downstream groove surfaces of air film hole exits well.In addition, air film
Cold air can be opened up to both sides to flowing in the rearward recess of hole, and which enhance the exhibitions of air film to covering.By above-mentioned 2 points of collective effect,
Gas film cooling efficiency is substantially increased, blade tip temperature is reduced.
Embodiment two：
Figure 10 is the schematic diagram of the embodiment two of the utility model blade tip groove gaseous film control structure.Figure 11 is E in Figure 10
Partial enlarged drawing.Figure 12 is the vertical view of the embodiment two of the utility model blade tip groove gaseous film control structure.Figure 13 is figure
The sectional view splitted along line C-C in 12.Figure 14 is the size of the embodiment two of the utility model blade tip groove gaseous film control structure
Schematic diagram.Figure 15 is the inclination angle schematic diagram of the embodiment two of the utility model blade tip groove gaseous film control structure.
As shown in Figure 10 to Figure 15, the utility model discloses a kind of blade tip groove air film hole cooling structures, are used for aviation
Engine turbine blade.The blade tip 30 of the aero engine turbine blades is disposed with several air film holes 31, each air film hole 31
Outlet be provided with expanding blade tip groove 32.Wherein, blade tip groove 32 includes two sides 321, front face 322 and bottom surface
323, two sides 321 herein symmetrically expand outwardly.The depth of the outlet initiating terminal of air film hole 31 is δ 1, the wall of blade tip 30
Thickness is δ, wherein 1≤2/3 δ of δ；The depth in 32 exit of blade tip groove is δ 2, and the value of δ 2 is determined by δ 1 and θ, wherein δ 2>0.This
The exit depth δ 2 of blade tip groove 32 is equal to the outlet initiating terminal depth δ 1 of air film hole 31 in embodiment.
Preferably, the setting of front face 322 of blade tip groove 32 is a flat surface in the present embodiment, and the width s of front face 322 is big
In the diameter d equal to air film hole 31.The front face 322 of blade tip groove 32 is at the lowest positions of the outlet of air film hole 31 and gas
The outlet profile of fenestra 31 is tangent.The value range for the angle ξ that the front face of blade tip groove 32 is formed with blade wall surface herein is excellent
The radial angle α of air film hole 31 is selected as to 90 °.The angle that the front face of blade tip groove 32 is formed with blade wall surface in the present embodiment
ξ is set as 90 °.
Two sides 321 of blade tip groove 32 and the outlet circular arc of air film hole 31 are tangent, and two sides of blade tip groove 32
Face 321 and the value range of the centerlines γ of air film hole 31 are preferably 10 ° -30 °.The radial angle α of air film hole 31 takes
Value ranges preferably from 20 ° -90 °, and the value range of the axial angle β of air film hole 21 is preferably 0 ° -90 °.Air film in the present embodiment
The axial angle β in hole 31 is set as 90 °.
Further, the angle theta that the center line of the bottom surface 323 of blade tip groove 32 and air film hole 31 is formed is less than or equal to air film
The radial angle α in hole 31.The angle theta etc. that the center line of the bottom surface 323 of blade tip groove 32 and air film hole 31 is formed in the present embodiment
In the radial angle α of air film hole 31.Herein, the angle theta that the center line of the bottom surface 323 of blade tip groove 32 and air film hole 31 is formed
Value range is preferably 5 ° -25 °.
In conclusion the utility model blade tip groove air film hole cooling structure is recessed in blade tip air film hole exits setting expanding
Slot structure, cold air is after air film hole ejection, and cold air can be dynamic close to groove wall flow along jet direction in groove, to reduce
The normal velocity component of jet stream so that air film can be attached to the downstream groove surfaces of air film hole exits well.In addition, air film
Cold air can be opened up to both sides to flowing in the rearward recess of hole, and which enhance the exhibitions of air film to covering.By above-mentioned 2 points of collective effect,
Gas film cooling efficiency is substantially increased, blade tip temperature is reduced.
Although the foregoing describe specific embodiment of the present utility model, it will be appreciated by those of skill in the art that
These are merely examples, and the scope of protection of the utility model is defined by the appended claims.Those skilled in the art
Member can make these embodiments numerous variations or repair under the premise of without departing substantially from the principles of the present invention and essence
Change, but these change and modification each fall within the scope of protection of the utility model.
Claims (10)
1. a kind of blade tip groove air film hole cooling structure is used for aero engine turbine blades, which is characterized in that the aviation hair
The blade tip of motivation turbo blade is disposed with several air film holes, and the outlet of each air film hole is provided with expanding blade tip groove,
The blade tip groove includes two sides, front face and bottom surface, and described two sides symmetrically expand outwardly；
The depth of the outlet initiating terminal of the air film hole is δ 1, and the wall thickness of the blade tip is δ, wherein 1≤2/3 δ of δ；The blade tip
Depth at recess outlet is δ 2, wherein δ 2>0.
2. blade tip groove air film hole cooling structure as described in claim 1, which is characterized in that two sides of the blade tip groove
Face and the outlet circular arc of the air film hole are tangent, two sides of the blade tip groove and the centerlines of the air film hole
Value range is 10 ° -30 °.
3. blade tip groove air film hole cooling structure as described in claim 1, which is characterized in that the radial angle of the air film hole
Value range be 20 ° -90 °, the value range of the axial angle of the air film hole is 20 ° -90 °.
4. blade tip groove air film hole cooling structure as claimed in claim 3, which is characterized in that the bottom surface of the blade tip groove with
The angle that the center line of the air film hole is formed is less than or equal to the radial angle of the air film hole.
5. blade tip groove air film hole cooling structure as claimed in claim 4, which is characterized in that the bottom surface of the blade tip groove with
The value range for the angle that the center line of the air film hole is formed is 5 ° -25 °.
6. blade tip groove air film hole cooling structure as claimed in claim 2, which is characterized in that the front face of the blade tip groove
For an arc surface.
7. blade tip groove air film hole cooling structure as claimed in claim 2, which is characterized in that the front face of the blade tip groove
It is a flat surface, the width of the front face is more than or equal to the diameter of the air film hole.
8. blade tip groove air film hole cooling structure as claimed in claim 7, which is characterized in that the front face of the blade tip groove
It is tangent with the outlet profile of the air film hole at the lowest positions of the outlet of the air film hole.
9. blade tip groove air film hole cooling structure as claimed in claim 8, which is characterized in that the front face of the blade tip groove
The angle formed with blade wall surface is 90 °.
10. blade tip groove air film hole cooling structure as claimed in claim 9, which is characterized in that the outlet of the blade tip groove
Locate the outlet initiating terminal depth δ 1 that depth δ 2 is equal to the air film hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721743030.7U CN207829957U (en) | 2017-12-14 | 2017-12-14 | Blade tip groove air film hole cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721743030.7U CN207829957U (en) | 2017-12-14 | 2017-12-14 | Blade tip groove air film hole cooling structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207829957U true CN207829957U (en) | 2018-09-07 |
Family
ID=63386226
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721743030.7U Active CN207829957U (en) | 2017-12-14 | 2017-12-14 | Blade tip groove air film hole cooling structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207829957U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109551068A (en) * | 2018-12-17 | 2019-04-02 | 中国航发沈阳发动机研究所 | A kind of rotor blade type face dustpan pore structure processing method and dustpan pore structure |
| CN113356932A (en) * | 2021-07-07 | 2021-09-07 | 西安交通大学 | Air film cooling composite hole structure for turbine blade and turbine blade |
| CN114810217A (en) * | 2021-01-27 | 2022-07-29 | 中国航发商用航空发动机有限责任公司 | Turbine rotor blade |
-
2017
- 2017-12-14 CN CN201721743030.7U patent/CN207829957U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109551068A (en) * | 2018-12-17 | 2019-04-02 | 中国航发沈阳发动机研究所 | A kind of rotor blade type face dustpan pore structure processing method and dustpan pore structure |
| CN114810217A (en) * | 2021-01-27 | 2022-07-29 | 中国航发商用航空发动机有限责任公司 | Turbine rotor blade |
| CN113356932A (en) * | 2021-07-07 | 2021-09-07 | 西安交通大学 | Air film cooling composite hole structure for turbine blade and turbine blade |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Bunker | A review of shaped hole turbine film-cooling technology | |
| Reiss et al. | Experimental study of showerhead cooling on a cylinder comparing several configurations using cylindrical and shaped holes | |
| Barigozzi et al. | Fan-shaped hole effects on the aero-thermal performance of a film-cooled endwall | |
| CN207829957U (en) | Blade tip groove air film hole cooling structure | |
| Rigby et al. | Improved film cooling effectiveness by placing a vortex generator downstream of each hole | |
| CN110259520A (en) | A kind of design method of shaped air film cooling hole | |
| CN107035421A (en) | A kind of turbine blade tail flow-disturbing with array pin rib partly splits seam cooling structure | |
| Barigozzi et al. | Effects of trenched holes on film cooling of a contoured endwall nozzle vane | |
| CN103452595A (en) | A Novel Air Film Hole for Improving Cooling Efficiency | |
| Acharya et al. | Numerical simulation of film cooling on the tip of a gas turbine blade | |
| Szwaba et al. | Roughness effect on shock wave boundary layer interaction area in compressor fan blades passage | |
| Wang et al. | An investigation for the turbine blade film cooling performance on the suction side tip region under rotating condition | |
| CN112523810B (en) | A triangular-column-shaped diversion structure applied to a half-split slit at the trailing edge of a turbine blade | |
| Liu et al. | Shock, leakage flow and wake interactions in a radial turbine with variable guide vanes | |
| CN112343667B (en) | Continuous V-shaped rib flow guide structure applied to turbine blade trailing edge half-splitting seam | |
| Nho et al. | Effects of tip shape on the gas turbine blade tip heat transfer | |
| Barigozzi et al. | End-wall film cooling through fan-shaped holes with different area ratios | |
| Mileshin et al. | Application of casing circumferential grooves to counteract the influence of tip clearance | |
| Asghar et al. | Investigation of a passive flow control device in an s-duct inlet of a propulsion system with high subsonic flow | |
| Li et al. | Implementation of rectangular vortex generator pairs to improve film cooling effectiveness on transonic rotor blade endwall | |
| Barigozzi et al. | Endwall film cooling effects on secondary flows in a contoured endwall nozzle vane | |
| Taremi et al. | Measurements of endwall flows in transonic linear turbine cascades: part II—high flow turning | |
| Zou et al. | Influence of blowing ratio and geometric parameters on cooling performance and thermal stress of a double wall structure | |
| Luo et al. | Thermal performance in latticework ducts with various endwall shapes for aero-craft turbine cooling | |
| Elston et al. | Leading edge jet impingement under high rotation numbers |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |