CN203362321U - Film hole used for cooling of gas turbine engine - Google Patents
Film hole used for cooling of gas turbine engine Download PDFInfo
- Publication number
- CN203362321U CN203362321U CN 201320342939 CN201320342939U CN203362321U CN 203362321 U CN203362321 U CN 203362321U CN 201320342939 CN201320342939 CN 201320342939 CN 201320342939 U CN201320342939 U CN 201320342939U CN 203362321 U CN203362321 U CN 203362321U
- Authority
- CN
- China
- Prior art keywords
- virtual cylinder
- cooling
- sides
- inducer
- hole
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 67
- 239000000411 inducer Substances 0.000 claims description 22
- 230000002146 bilateral effect Effects 0.000 claims description 3
- 230000001788 irregular Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 4
- 238000005452 bending Methods 0.000 abstract 2
- 238000002485 combustion reaction Methods 0.000 abstract 1
- 238000007664 blowing Methods 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 2
- 210000003734 kidney Anatomy 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A film hole used for the cooling of a gas turbine engine can be applied to the cooling of high-temperature components of a combustion chamber, a turbine and the like of the gas turbine engine. The film hole comprises an inlet section and an expansion section, wherein the inlet section is a cylinder hole; the expansion section is formed by the mutual stacking and connection of two side virtual cylinders formed by expanding into two sides firstly and then bending forwards, and a middle virtual cylinder formed by the extending of the inlet section; the connection manner of the two side virtual cylinders and the middle virtual cylinder adopts the manner that two ends of a straight line is tangentially connected with the middle virtual cylinder and the two side virtual cylinders respectively, or adopts the manner that two ends of a multistage broken line and a curve are tangentially connected with the middle virtual cylinder and the two side virtual cylinders respectively, and a chamfering is formed in an included angle part. The film hole expands through the outlet side direction to increase the side direction coverage area; meanwhile, the flow field structure of the film cooling is facilitated through the bending forward structure of the two side virtual cylinders, so that the film cooling effect is improved integrally.
Description
Technical field
The utility model relates to gas turbine engine, specifically comprise heavy single shift gas turbine, aeroengine and naval vessel gas turbine etc., it is the Novel hole structure of a kind of discrete holes air film cooling (annotating: also referred to as film cooling), can improve the gas film cooling efficiency of the high temperature parts such as gas-turbine unit turbine, firing chamber, the air film that is applicable to all discrete holes forms is cooling.
Background technique
The operating temperature of modern gas turbine engines all surpasses the withstand temperature of metallic material.Air film is cooling as a kind of efficient type of cooling, and the high-temperature component that is widely used in heavy duty gas turbine, aeroengine and naval vessel gas turbine is cooling.Air film is cooling is cooled gas jet from one or more discrete holes, at wall, forms one deck gas membrane to protect wall not by the high-temperature gas ablation.In gas turbine engine, for cooling air, be generally the pressurized air of extracting out from the gas compressor corresponding stage, the height of gas film cooling efficiency is directly connected to the size of air supply, thereby affects operational efficiency and the performance of complete machine.Air film is cooling be two burst different temperatures fluid mutual blending leading by convection current and with the convection heat exchange problem of cooling wall, and the key that improves gas film cooling efficiency is to limit cold air to blow off with cooling wall from air film hole ejects, enlarge the area coverage of cooled gas at wall simultaneously, particularly enlarge the side direction coverage area of cold air; Therefore, particularly important with the formed flow field structure of high temperature main flow after cool air injection.Traditional cylinder type air film hole has formed kidney shape vortex pair in the air film coolant flow field, and this vortex system structure makes cold air and cooling wall blow off under the high temperature main flow is involved in to the cold air jet from both sides, causes the deterioration of cooling effect; And traditional forming hole has enlarged the area of hole exits, reduced the outlet momentum of impinging jet of cold air, thereby weakened the generation in kidney shape whirlpool, in addition because discharge area enlarges the side direction coverage area that has increased cold air, thereby obtained the Film Cooling more had with respect to cylindrical hole, still traditional forming hole also still can't initiatively produce and be conducive to the cooling flow field vortex system structure of air film; Be conducive to the cooling flow field vortex system structure of air film in order to construct subsequently, by experts and scholars, two or more cylindrical holes are formed to an air film hole unit, as jet hole, tripod hole etc., however the air film hole structure that these porous form exists the difficulty of manufacturing aspect to reach the deficiency that is difficult to aspects such as being applied under the air supply space condition limited at blade.
The model utility content
The purpose of this utility model is to disclose a kind of air film hole cooling for gas turbine engine, to improve the gas film cooling efficiency of gas turbine engine.
The technical solution of the utility model is as follows:
A kind of air film hole cooling for gas turbine engine, it is characterized in that: this air film hole comprises inducer and extending section, inducer is cylindrical hole, extending section is formed by connecting by intermediate virtual cylinder and both sides virtual cylinder, be specially: extending section be take the inducer end center of circle and is started to expand to bilateral symmetry as initial point, form and the isodiametric both sides of inducer virtual cylinder, both sides virtual cylinder center line and inducer center line form angle β, the both sides virtual cylinder be take the inducer end center of circle and is leaned forward as initial point subsequently, form top rake γ on the front elevation projection plane with the intermediate virtual cylinder, both sides virtual cylinder and intermediate virtual cylinder mutually superpose and are connected to form extending section, the Placement of both sides virtual cylinder and intermediate virtual cylinder adopts the straight line two ends respectively with the intermediate virtual cylinder and the both sides virtual cylinder is tangent is connected, or employing multistage broken line, the curve two ends are respectively with the intermediate virtual cylinder and the both sides virtual cylinder is tangent is connected, and form the chamfering of circular arc or irregular curvature in angle.
Air film hole entrance length L of the present utility model
1with the hole total length L
0ratio delta between 0～1, general span is between 1/3 to 2/3; The span of the both sides angle β of both sides virtual cylinder and intermediate virtual cylinder is 8 °～25 °, and the span of top rake γ is 1 °～4.5 °; The angle of this air film hole and cooling wall in use, efflux angle is 20 °～60 °.
The utlity model has the technique effect of following advantage and high-lighting: this film cooling holes structure can be beneficial to the advantage that cooling flow field vortex system structure two great tradition forming hole and the porous combinations of air film are had respectively and rolls into one enlarging cold air side direction coverage area and being configured with, this air film hole is expanded and is increased the hole exits area by both sides, thereby increase the side direction coverage area of cold air, simultaneously by virtual cylinder hole, both sides lean forward and with being smoothly connected of intermediate virtual cylindrical hole, construct and be conducive to the cooling flow field structure of air film, thereby the whole Film Cooling that improves, testing and show by film cooling, is under 1.0 and 1.5 conditions at density ratio, and in blowing, than being in 0.5～2.0 scope, the zone leveling gas film cooling efficiency of film cooling holes of the present utility model can improve 20%～40% than traditional forming hole.
The accompanying drawing explanation
Fig. 1 be of the present utility model a kind of for gas turbine engine the schematic three dimensional views of cooling air film hole.
The plan view that Fig. 2 is film cooling holes of the present utility model.
The front elevation that Fig. 3 is film cooling holes of the present utility model.
Fig. 4 is the sectional view of film cooling holes of the present utility model perpendicular to axially bored line.
The axially bored line sectional view that Fig. 5 is the similar structural change of film cooling holes topology of the present utility model.
Fig. 6 is the schematic diagram that film cooling holes of the present utility model is applied to film cooling.
Fig. 7 be film cooling holes of the present utility model for the experimental measurements of film cooling and with the comparing result of the traditional forming hole of identical operating mode.
Embodiment
Below in conjunction with accompanying drawing, structure of the present utility model, principle and performance are described:
The utility model is a kind of cooling hole structure of gas turbine engine type air film that is applicable to, its basic cell structure is as shown in Figure 1: this air film hole comprises inducer 1 and extending section 2, inducer 1 is cylindrical hole, extending section 2 is formed by connecting by intermediate virtual cylinder 3 and both sides virtual cylinder 4, be specially: extending section 2 be take the inducer 1 end center of circle and is started to expand to bilateral symmetry as initial point, form and the isodiametric both sides of inducer virtual cylinder 4, both sides virtual cylinder 4 center lines and inducer 1 center line form angle β, as shown in Figure 2; Both sides virtual cylinder 4 be take the inducer 1 end center of circle as initial point leans forward subsequently, forms top rake γ with intermediate virtual cylinder 3, as shown in Figure 3 on the front elevation projection plane; Both sides virtual cylinder 4 mutually superposes and is connected to form extending section 2 with intermediate virtual cylinder 3, the Placement of both sides virtual cylinder 4 and intermediate virtual cylinder 3 adopts the straight line two ends respectively with intermediate virtual cylinder 3 and both sides virtual cylinder 4 is tangent is connected, or adopt multistage broken line, curve two ends respectively with intermediate virtual cylinder 3 and both sides virtual cylinder 4 is tangent is connected, and form the chamfering of circular arc or irregular curvature in angle, as shown in Figure 4; What Fig. 5 showed is the air film hole vertical axis schematic cross-section that intermediate virtual cylinder 3 is connected by broken line with both sides virtual cylinder 4 and forms when the end angle adopts circular arc chamfering.The length of this air film hole inducer 1 is L
1,, the length of extending section is L
2,, the length of inducer is L
1with the hole total length L
0ratio delta between 0 to 1, general value is between 1/3 to 2/3; Both sides virtual cylinder 4 is 8 °～25 ° with the span of the both sides angle β of intermediate virtual cylinder 3, and the span of top rake γ is 1 °～4.5 °; The angle of this air film hole and cooling wall in use, efflux angle α is generally 20 °～60 °.
Fig. 6 is the application example of New Gas Film hole structure of the present utility model on film cooling, and in this application example, the efflux angle α of this air film hole is 30 °.Flow through air film hole ejection of cooled gas 5, form film overcasts on cooling wall 6 surfaces, simultaneously dissipation final with the mutual blending of high temperature main flow 7.The film overcast effect directly depends on the shape of plasma jet of cold airflow after air film hole and the flow field structure in air film district, downstream.Air film hole of the present utility model is expanded and is increased the hole exits area by both sides, thereby increase the side direction coverage area of cold air, simultaneously by both sides virtual cylinder 4 lean forward and with being smoothly connected of intermediate virtual cylinder 3, construct and be conducive to the cooling flow field structure of air film, thus the whole Film Cooling that improves.The ratio delta of inducer 1 length and hole total length, lateral spread angle beta and both sides top rake γ are the main characteristic parameters of film cooling holes of the present utility model, are also the key parameters that affects its air film cooling performance.
Fig. 7 is the experimental measurements that film cooling holes of the present utility model is applied to film cooling, and experiment condition is that density ratio is 1.0 and 1.5, and blowing is than being 0.5～2.0, and experiment compares under identical working condition with traditional forming hole simultaneously.Curve 8 and curve 9 are respectively that air film hole is the zone leveling gas film cooling efficiency under 1.0 and 1.5 conditions at density ratio, curve 10 and curve 11 are respectively that traditional forming hole is the zone leveling gas film cooling efficiency under 1.0 and 1.5 conditions at density ratio, contrast the zone leveling gas film cooling efficiency of air film hole of this model utility and the zone leveling gas film cooling efficiency of traditional forming hole, and the zone leveling gas film cooling efficiency of the zone leveling gas film cooling efficiency of air film hole of the present utility model and traditional forming hole, result shows, at density ratio, be under 1.0 and 1.5 conditions, in blowing than being in 0.5～2.0 scope, the zone leveling gas film cooling efficiency of film cooling holes of the present utility model can improve 20%～40% than traditional forming hole.
Claims (3)
1. an air film hole cooling for gas turbine engine, it is characterized in that: this air film hole comprises inducer (1) and extending section (2), inducer (1) is cylindrical hole, extending section (2) is formed by connecting by intermediate virtual cylinder (3) and both sides virtual cylinder (4), be specially: extending section be take inducer (1) the end center of circle and is started to expand to bilateral symmetry as initial point, form and the isodiametric both sides of inducer virtual cylinders (4), both sides virtual cylinder (4) center line and inducer (1) center line form angle β, both sides virtual cylinder (4) be take inducer (1) the end center of circle and is leaned forward as initial point subsequently, form top rake γ on the front elevation projection plane with intermediate virtual cylinder (3), both sides virtual cylinder (4) mutually superposes and is connected to form extending section (2) with intermediate virtual cylinder (3), the Placement of both sides virtual cylinder (4) and intermediate virtual cylinder (3) adopt the straight line two ends respectively with intermediate virtual cylinder (3) and tangent connection of both sides virtual cylinder (4), or employing multistage broken line, the curve two ends respectively with intermediate virtual cylinder (3) and tangent connection of both sides virtual cylinder (4), and form the chamfering of circular arc or irregular curvature in angle.
2. according to a kind of air film hole cooling for gas turbine engine claimed in claim 1, it is characterized in that: the length L of the inducer of described air film hole (1)
1with the hole total length L
0ratio delta between 0～1; Both sides virtual cylinder (4) is 8 °～25 ° with the span of the both sides angle β of intermediate virtual cylinder (3), and the span of top rake γ is 1 °～4.5 °.
3. according to a kind of air film hole cooling for gas turbine engine claimed in claim 2, it is characterized in that: the length L of the inducer of described air film hole (1)
1with the hole total length L
0ratio delta between 1/3 to 2/3; The angle of this air film hole and cooling wall in use, efflux angle is 20 °～60 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320342939 CN203362321U (en) | 2013-06-14 | 2013-06-14 | Film hole used for cooling of gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320342939 CN203362321U (en) | 2013-06-14 | 2013-06-14 | Film hole used for cooling of gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203362321U true CN203362321U (en) | 2013-12-25 |
Family
ID=49810103
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320342939 Expired - Lifetime CN203362321U (en) | 2013-06-14 | 2013-06-14 | Film hole used for cooling of gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203362321U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103291459A (en) * | 2013-06-14 | 2013-09-11 | 清华大学 | Gas film hole used for cooling gas turbine engine |
-
2013
- 2013-06-14 CN CN 201320342939 patent/CN203362321U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103291459A (en) * | 2013-06-14 | 2013-09-11 | 清华大学 | Gas film hole used for cooling gas turbine engine |
| CN103291459B (en) * | 2013-06-14 | 2016-02-24 | 清华大学 | A kind of air film hole for gas turbine engine cooling |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103291459B (en) | A kind of air film hole for gas turbine engine cooling | |
| CN103437889B (en) | A kind of branch's film hole structure for gas turbine engine cooling | |
| US9810073B2 (en) | Turbine blade having swirling cooling channel and cooling method thereof | |
| CN103244196B (en) | Discrete air film cooling hole shape | |
| CN105180211B (en) | Combustion chamber and scramjet engine with Cavity Flame Holder | |
| CN104791848A (en) | Combustion chamber flame cylinder wall face with blade grid channel multi-inclined-hole cooling manner adopted | |
| US20150204197A1 (en) | Airfoil leading edge chamber cooling with angled impingement | |
| CN107503801A (en) | A kind of efficiently array jetting cooling structure | |
| JP6506549B2 (en) | Structural configuration and cooling circuit in turbine blade | |
| CN110081466A (en) | A kind of burner inner liner wall structure cooling using microchannel | |
| CN203362321U (en) | Film hole used for cooling of gas turbine engine | |
| CN112577070A (en) | Low-resistance and high-efficiency scramjet engine thrust chamber integrated design method | |
| CN105298649B (en) | A kind of gaseous film control pore structure for gas-turbine unit thin-walled hot-end component | |
| US20170145835A1 (en) | Turbine airfoil cooling system with bifurcated mid-chord cooling chamber | |
| CN113356932B (en) | Air film cooling composite hole structure for turbine blade and turbine blade | |
| CN204404235U (en) | A kind of gas-turbine combustion chamber changeover portion with cooling structure | |
| CN204648317U (en) | A kind of gas-turbine combustion chamber burner inner liner with cooling structure | |
| CN105840315B (en) | A kind of eddy flow cold air cavity configuration applied to air film cooling technology | |
| CN113958372A (en) | Micro-rib and film hole combined cooling structure for turbine guide end wall | |
| CN112761733A (en) | Cross air film cooling hole structure capable of inhibiting development of kidney-shaped vortex pairs and application thereof | |
| KR101682639B1 (en) | Gas Turbine Vane and Blade Having Cooling Passage Added on Outermost Surface | |
| CN104100380A (en) | Heat exchange method of mainstream gas of aero-engine | |
| CN115898554B (en) | Air film hole structure of turbine blade | |
| CN114562339B (en) | Leakage groove air film cooling structure with protrusions for turbine end wall and application | |
| CN114046180B (en) | Combined hole air film cooling structure utilizing rotational flow |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20131225 Effective date of abandoning: 20160224 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |