CN105298649A - Gas film cooling hole structure used for thin-walled hot end part of gas turbine engine - Google Patents
Gas film cooling hole structure used for thin-walled hot end part of gas turbine engine Download PDFInfo
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- CN105298649A CN105298649A CN201510810965.1A CN201510810965A CN105298649A CN 105298649 A CN105298649 A CN 105298649A CN 201510810965 A CN201510810965 A CN 201510810965A CN 105298649 A CN105298649 A CN 105298649A
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- hole
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- heart
- film cooling
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Abstract
The invention discloses a gas film cooling hole structure used for a thin-walled hot end part of a gas turbine engine and belongs to the technical field of gas turbine engines. The gas film cooling hole comprises an inlet segment and a pit segment; the inlet segment is a cylindrical hole; the pit segment is formed by connecting a pit segment body shaped like a Chinese character 'xin' and located on the hole leeward with a semi-cylindrical pit segment body located on the hole windward face; starting from the tail end circle center, serving as an original point, of the inlet segment, the pit segment starts to expand to the hole windward face to form the semi-cylindrical pit segment body, and expand to the hole leeward to form the pit segment body shaped like the Chinese character 'xin'; and the pit segment body shaped like the Chinese character 'xin' and the semi-cylindrical pit segment body use an outlet cross section center point of the cylindrical hole as a demarcation point. The gas film cooling hole has the beneficial effects that the outlet area of the gas film cooling hole can be increased, the cold gas outlet momentum is reduced, and the cold gas covering effect is enhanced; and inverted-kidney-shaped vortexes are generated through the pit segment body shaped like the Chinese character 'xin' and located on the leeward of the pit segment, a flow field structure favorable for gas film cooling coverage is constructed, and the wall face can be better covered with cooling fluid.
Description
Technical field
The present invention relates to gas turbine engine, specifically comprise heavy single shift gas turbine, aeroengine and Vessel personnel etc., it is the Novel hole structure of a kind of discrete holes gaseous film control (note: also referred to as film cooling), the gas film cooling efficiency of the high-temperature components such as gas turbine engine turbine, firing chamber can be improved, be applicable to the gaseous film control of all discrete holes forms, and be applicable to thin-walled hot-end component.
Background technique
The operating temperature of modern gas turbine engines has exceeded the withstand temperature of metallic material all.Gaseous film control, as the efficient type of cooling of one, is widely used in the high-temperature component cooling of heavy duty gas turbine, aeroengine and Vessel personnel.Gaseous film control is cooled gas jet from one or more discrete holes, forms one deck gas membrane to protect wall not by high-temperature gas ablation at wall.In gas turbine engine, the air for cooling is generally the pressurized air extracted out from gas compressor corresponding stage, and the height of gas film cooling efficiency is directly connected to the size of air supply, thus affects operational efficiency and the performance of complete machine.Gaseous film control is the two bursts of mutual blending of different temperatures fluid and the convection heat exchange problem with cooling wall dominated by convection current, and the key improving gas film cooling efficiency is that restriction cold air ejects afterwards from air film hole and cooling wall blows off, expand cooled gas in the area coverage of wall simultaneously, particularly expand the side direction coverage area of cold air; Therefore, the flow field structure formed with high temperature main flow after cool air injection is particularly important.Traditional cylinder type air film hole defines kidney shape vortex pair in gaseous film control flow field, and high temperature main flow is involved under Gas Cooling from both sides by this vortex structures, cold air and cooling wall is blown off, causes the deterioration of cooling effect; And traditional forming hole expands the area of hole exits, reduce the outlet jet momentum of cold air, thus weaken the generation in kidney shape whirlpool, the side direction coverage area of cold air is added in addition because discharge area expands, thus obtain the Film Cooling more had relative to cylindrical hole, but traditional forming hole also still initiatively cannot produce the flow field vortex structures being conducive to gaseous film control; Subsequently in order to construct the flow field vortex structures being conducive to gaseous film control, by experts and scholars, two or more cylindrical holes are formed an air film hole unit, as jet hole, tripod frame aperture etc., however the difficulty and being difficult under the limited air supply space condition of blade that the gaseous film control hole structure of these porous composition exists manufacturing aspect to be applied etc. in deficiency.In addition, along with combustion gas turbine hot-end component, as firing chamber and turbine blade, start the trend turning to thin-walled to cool gradually, wall thickness is thinning brings huge obstacle to the processing of the film cooling holes of the complicated shapes such as forming hole, and forming hole is processed cannot carry out smoothly.
Summary of the invention
The object of the invention is openly a kind of crater type gaseous film control hole structure for gas turbine engine thin-walled hot-end component, to improve the gas film cooling efficiency of gas turbine engine.
Technological scheme of the present invention is as follows:
A kind of gaseous film control hole structure for gas turbine engine thin-walled hot-end component, it is characterized in that: this film cooling holes comprises inducer and pit section, inducer is cylindrical hole, and " heart " pit section of pit Duan Youkong lee face and the semicolumn pit section of windward side, hole are formed by connecting; Described pit section for initial point starts with the inducer end center of circle, stretches to windward side, hole and forms semicolumn pit section, and stretching to hole lee face forms " heart " pit section; " heart " pit section and semicolumn pit section are for separation with the outlet central point of cylindrical hole.
In technique scheme, the curve controlled parameter of described " heart " pit section comprises the control angle β that tangent line MR that following four: a. cylindrical hole sideline MN and " heart " pit section cross a M is formed
1between 120 ° ~ 160 °; B. " heart " pit section crosses the control angle β that the tangent line OP of an O and cylindrical hole medial axis are formed
2between 30 ° ~ 60 °; C. the max-flow of " heart " pit section (3) flows to coordinate value difference X to the max-flow of coordinate points A and inducer (1) to coordinate points O
1between 0.1D ~ 0.5D, D is the diameter of inducer; D. the max-flow of inducer (1) is to the side direction coordinate value difference Y of the maximum side direction coordinate points B of coordinate points O and " heart " pit section (3)
1between 0.6D ~ 0.9D.
Preferably, the length L of described inducer
1with the normal direction length L of pit section
2ratio delta be between 2 ~ 4; The angle α of this film cooling holes and cooling wall and efflux angle are 20 ° ~ 60 °.
The present invention has the following advantages and the technique effect of high-lighting: 1. film cooling holes of the present invention remains the low advantage of traditional round tee section film cooling holes processing cost, utilizes thermal barrier coating or electric discharge machining to go out " heart " crater in cylindrical hole exit portion; Compared to traditional circular hole and forming hole, crater air film hole has 2 advantages, and one is to increase film cooling holes discharge area, reduces cold air outlet momentum, strengthens cold air coverage effect, and two is reduce difficulty of processing; 2. utilize " heart " pit of pit section lee face to produce anti-kidney type whirlpool, construct the flow field structure being conducive to gaseous film control and covering, make cooling fluid have better covering at wall.
Accompanying drawing explanation
Fig. 1 is the schematic three dimensional views of crater of the present invention type gaseous film control hole structure.
Fig. 2 is the plan view of crater of the present invention type film cooling holes.
Fig. 3 is the front elevation of crater of the present invention type film cooling holes.
Fig. 4 is the schematic three dimensional views of the crater type gaseous film control hole structure of another distortion of the present invention.
Fig. 5 is the structural representation that crater of the present invention type film cooling holes is applied to film cooling.
In figure: 1 – inducer; 2 – pit sections; 3-" heart " pit section; 4-semicolumn pit section; 5-cooled gas; 6 – are cooled wall; 7-high temperature mainstream gas.
Embodiment
Below in conjunction with accompanying drawing, structure of the present invention, principle and performance are described:
The present invention is a kind of gaseous film control hole structure for gas turbine engine thin-walled hot-end component, its basic geometric properties as shown in Figure 1, Figure 2 and Figure 3.This film cooling holes comprises inducer 1 and pit section 2, inducer is cylindrical hole, pit section 2 is formed by connecting by " heart " pit section 3 of hole lee face and the semicolumn pit section 4 of windward side, hole, described pit section 2 with the inducer 1 end center of circle for initial point starts, stretch to windward side, hole and form semicolumn pit section 4, stretching to hole lee face forms " heart " pit section 3; " heart " pit section 3 and semicolumn pit section 4 are for separation with the outlet central point of cylindrical hole.
Fig. 2 is the plan view of the flow passage component of crater type film cooling holes.The curve controlled parameter of " heart " pit section 3 comprises following four: a. cylindrical hole sideline MN and " heart " pit section 3 and crosses the control angle β that the tangent line MR that puts M formed
1between 120 ° ~ 160 °; B. " heart " pit section 3 crosses the control angle β that the some tangent line OP of O and cylindrical hole medial axis are formed
2between 30 ° ~ 60 °; C. the max-flow of " heart " pit section (3) flows to coordinate value difference X to the max-flow of coordinate points A and inducer (1) to coordinate points O
1between 0.1D ~ 0.5D, D is the diameter of inducer; D. the max-flow of inducer (1) is to the side direction coordinate value difference Y of the maximum side direction coordinate points B of coordinate points O and " heart " pit section (3)
1between 0.6D ~ 0.9D: the length L of inducer 1
1with the normal direction length L of pit section 2
2ratio delta value be between 2 ~ 4; The angle α of this film cooling holes and cooling wall and efflux angle are 20 ° ~ 60 °.
Fig. 4 is the schematic three dimensional views of the flow passage component of another crater type gaseous film control hole structure of the present invention.This film cooling holes keeps the shape the same with " heart " crater film cooling holes substantially, and the part of change only has " heart " pit section 3 in Fig. 1.In Fig. 4, there is the sudden change of lateral width at arc pit section 3 and semicolumn pit section 4 interface place, and then arc pit section 3 is transitioned into lee face gradually; This film cooling holes can effectively be expanded export area, improves film cooling holes validity.
Fig. 5 is the application example of gaseous film control hole structure of the present invention on film cooling.Cooled gas 5 flows through film cooling holes of the present invention ejection, forms film overcast on cooled wall 6 surface, simultaneously with high temperature mainstream gas 7 blending and finally dissipating mutually.Film overcast effect directly depends on the shape of plasma jet of cold airflow after film cooling holes and the flow field structure in air film district, downstream.
New Gas Film Cooling Holes of the present invention, by increasing hole exits area, increases gaseous film control coverage area; Go out to flow the mutual interference between cold air by film cooling holes " heart " pit, construct the flow field structure being conducive to gaseous film control and covering, make cooling fluid have better coverage effect at wall.The ratio delta of entrance length and hole total length, the control angle β of " heart " pit spline curve
1, β
2with command range X
1, Y
1being the main characteristic parameters of film cooling holes of the present invention, is also the key parameter affecting its gaseous film control performance.
Claims (3)
1. the gaseous film control hole structure for gas turbine engine thin-walled hot-end component, it is characterized in that: this film cooling holes comprises inducer (1) and pit section (2), inducer is cylindrical hole, and pit section (2) is formed by connecting by " heart " pit section (3) of hole lee face and the semicolumn pit section (4) of windward side, hole; Described pit section (2) is that initial point starts with inducer (1) the end center of circle, and stretching to windward side, hole forms semicolumn pit section (4), and stretching to hole lee face forms " heart " pit section (3); " heart " pit section (3) and semicolumn pit section (4) are for separation with the outlet central point of cylindrical hole.
2. according to a kind of gaseous film control hole structure for gas turbine engine thin-walled hot-end component according to claim 1, it is characterized in that: the curve controlled parameter of described " heart " pit section (3) comprises following four:
A. the control angle β that the tangent line MR that cylindrical hole sideline MN and " heart " pit section (3) cross some M is formed
1between 120 ° ~ 160 °;
B. " heart " pit section (3) crosses the control angle β that the some tangent line OP of O and cylindrical hole medial axis are formed
2between 30 ° ~ 60 °;
C. the max-flow of " heart " pit section (3) flows to coordinate value difference X to the max-flow of coordinate points A and inducer (1) to coordinate points O
1between 0.1D ~ 0.5D, D is the diameter of inducer;
D. the max-flow of inducer (1) is to the side direction coordinate value difference Y of the maximum side direction coordinate points B of coordinate points O and " heart " pit section (3)
1between 0.6D ~ 0.9D.
3., according to a kind of gaseous film control hole structure for gas turbine engine thin-walled hot-end component described in claim 1 or 2, it is characterized in that: the length L of described inducer (1)
1with the normal direction length L of pit section (2)
2ratio delta value be between 2 ~ 4; The angle α of this film cooling holes and cooling wall and efflux angle are 20 ° ~ 60 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510810965.1A CN105298649B (en) | 2015-11-20 | 2015-11-20 | A kind of gaseous film control pore structure for gas-turbine unit thin-walled hot-end component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510810965.1A CN105298649B (en) | 2015-11-20 | 2015-11-20 | A kind of gaseous film control pore structure for gas-turbine unit thin-walled hot-end component |
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| Publication Number | Publication Date |
|---|---|
| CN105298649A true CN105298649A (en) | 2016-02-03 |
| CN105298649B CN105298649B (en) | 2017-10-03 |
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|---|---|---|---|
| CN201510810965.1A Active CN105298649B (en) | 2015-11-20 | 2015-11-20 | A kind of gaseous film control pore structure for gas-turbine unit thin-walled hot-end component |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112443361A (en) * | 2020-11-04 | 2021-03-05 | 西北工业大学 | A reverse air film pore structure of pit for turbine blade |
| CN114856715A (en) * | 2022-05-12 | 2022-08-05 | 沈阳航空航天大学 | Boss and pit combined type blade air film cooling hole structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2554792A1 (en) * | 2010-03-24 | 2013-02-06 | Kawasaki Jukogyo Kabushiki Kaisha | Double-jet film cooling structure |
| CN103244196A (en) * | 2012-02-08 | 2013-08-14 | 中国科学院工程热物理研究所 | Discrete air film cooling hole shape |
| CN103291459A (en) * | 2013-06-14 | 2013-09-11 | 清华大学 | Gas film hole used for cooling gas turbine engine |
| WO2014189092A1 (en) * | 2013-05-22 | 2014-11-27 | 川崎重工業株式会社 | Double-jet film cooling structure and method for manufacturing same |
| CN104879171A (en) * | 2015-05-08 | 2015-09-02 | 西北工业大学 | Y-shaped air film hole structure used for turbine blade |
-
2015
- 2015-11-20 CN CN201510810965.1A patent/CN105298649B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2554792A1 (en) * | 2010-03-24 | 2013-02-06 | Kawasaki Jukogyo Kabushiki Kaisha | Double-jet film cooling structure |
| CN103244196A (en) * | 2012-02-08 | 2013-08-14 | 中国科学院工程热物理研究所 | Discrete air film cooling hole shape |
| WO2014189092A1 (en) * | 2013-05-22 | 2014-11-27 | 川崎重工業株式会社 | Double-jet film cooling structure and method for manufacturing same |
| CN103291459A (en) * | 2013-06-14 | 2013-09-11 | 清华大学 | Gas film hole used for cooling gas turbine engine |
| CN104879171A (en) * | 2015-05-08 | 2015-09-02 | 西北工业大学 | Y-shaped air film hole structure used for turbine blade |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112443361A (en) * | 2020-11-04 | 2021-03-05 | 西北工业大学 | A reverse air film pore structure of pit for turbine blade |
| CN114856715A (en) * | 2022-05-12 | 2022-08-05 | 沈阳航空航天大学 | Boss and pit combined type blade air film cooling hole structure |
| CN114856715B (en) * | 2022-05-12 | 2024-05-10 | 沈阳航空航天大学 | Boss and pit combined type blade air film cooling hole structure |
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| Publication number | Publication date |
|---|---|
| CN105298649B (en) | 2017-10-03 |
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