CN216043898U - Combined structure air film hole for cooling front edge of turbine blade - Google Patents
Combined structure air film hole for cooling front edge of turbine blade Download PDFInfo
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- CN216043898U CN216043898U CN202122506651.6U CN202122506651U CN216043898U CN 216043898 U CN216043898 U CN 216043898U CN 202122506651 U CN202122506651 U CN 202122506651U CN 216043898 U CN216043898 U CN 216043898U
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a combined structure air film hole for cooling the front edge of a turbine blade, which comprises a first through hole and a tapered hole which are sequentially communicated from the inlet direction to the outlet direction, wherein the first through hole and the tapered hole are arranged in a non-coaxial manner, and the cross section area of the outlet of the tapered hole is larger than that of the first through hole; the axial lead of the first through hole is a straight line; the inner wall surface of the first through hole and the inner wall surface of the conical hole have no edges and corners. The utility model can form a better cooling air film on the front edge of the blade, the first through hole realizes the control of the cooling air flow, the tapered hole increases the outlet area of the air film hole, reduces the speed of cooling air at the outlet of the air film hole, improves the covering effect of the cooling air flow, obviously improves the cooling effect of the blade, reduces the temperature of the wall surface of the front edge of the blade, passivates the sharp edge at the outlet edge of the air film hole, improves the stress concentration coefficient of the outlet edge of the air film hole, reduces the stress of the outlet edge of the air film hole, is beneficial to reducing the temperature of the wall surface of the blade, improving the reliability of the blade and prolonging the service life of the blade.
Description
Technical Field
The utility model belongs to the technical field of gas turbines and aero-engines, and particularly relates to a combined structure air film hole for cooling the front edge of a turbine blade.
Background
In high performance gas turbines, the turbine front gas temperature is much higher than the material temperature used for the turbine blades, especially the turbine blade leading edge experiences the highest gas temperature, and in order to reduce the temperature of the wall surface in the blade leading edge area, it is usually necessary to perform film cooling on the leading edge of the gas turbine blade. In order to ensure that cooling air at the front edge of the blade can be exhausted through the film hole under various states, a higher cooling air pressure margin is usually selected, but the cooling air pressure exhausted from the film hole needs to be matched with the gas pressure of the outer surface of the blade, if the cooling air pressure is too low, the cooling air can not be exhausted from the film hole, even gas is generated to enter the blade, and then the blade can be ablated and failed in a short time. At present, the gas film holes on the front edges of the gas turbine blades are generally cylindrical, and the gas film holes are simple in structure and convenient to process, but because cold air pressure and gas pressure are difficult to match, effective gas film covering is difficult to form in the front edge area of the blades by cooling air, and the gas film cooling effect is low.
In order to improve the air film cooling effect of the front edge of the turbine blade, the flow speed of cooling air at the outlet of an air film hole needs to be reduced on the premise of ensuring the air pressure margin of the cooling air of the air film hole of the blade, so that the cooling air can better cover the wall surface of the front edge of the blade. At present, a cylindrical air film hole is still adopted in the front edge area of the blade, and the flow velocity of cooling air at the outlet of the air film hole is reduced by commonly using a method for expanding the cross section area of the outlet of the air film hole in the basin and back areas of the blade, namely, the shape of the outlet of the air film hole is gradually expanded into a rectangular structure from the cylindrical structure, so that the speed of the outlet of the cooling air flow is greatly reduced, and the covering effect of the cooling air flow on the outer surfaces of the basin and the back areas of the blade is improved. The structural film hole is applied to an advanced high-temperature gas turbine, but is not suitable for film cooling of the leading edge area of the blade. The profile curvature of the front edge area of the blade is large, the diameter of the front edge area of the blade is small, the air film hole with a rectangular structure is difficult to manufacture, and in addition, the rectangular hole is easy to generate stress concentration and is not suitable for the front edge of the blade, particularly for air film cooling of the front edge of the rotor blade.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a combined structure air film hole for cooling the front edge of a turbine blade, which is used for improving the air film cooling effect of the front edge of the turbine rotor blade and solving the problem of air film cooling of a cylindrical air film hole at the front edge of the blade.
In order to achieve the purpose, the utility model adopts the following technical scheme:
a composite structure air film hole for cooling the leading edge of a turbine blade comprises a first through hole and a tapered hole which are sequentially communicated from the inlet direction to the outlet direction, wherein the first through hole and the tapered hole are arranged in a non-coaxial mode, and the cross section area of the outlet of the tapered hole is larger than that of the cross section of the first through hole; the axial lead of the first through hole is a straight line; the inner wall surface of the first through hole and the inner wall surface of the conical hole are not provided with edges and corners.
As a specific implementation manner, it needs to be further explained in this implementation manner that the tapered hole is a conical hole with a circular cross section. Circular through-hole processing is convenient, and the internal wall does not have any edges and corners structure, when air conditioning gets into in the first through-hole of circular through-hole form, can not produce extra stress.
As a specific implementation manner, it needs to be further explained in this implementation manner that the taper angle of the tapered hole is not less than 10 °, specifically may be 10 °, 30 °, 50 °, 70 °, or 80 °, and the taper angle of the tapered hole is usually less than 120 °, so as long as the taper angle of the tapered hole is within a range of greater than or equal to 10 ° and less than 120 °, which may be determined according to practical situations and is not specifically limited, and the diameter of the air outlet may be increased within the same length, so as to meet the requirement that the diameter of the air outlet of the tapered hole is greater than the diameter of the first through hole, thereby forming a better cooling air film at the leading edge of the blade, significantly improving the cooling effect of the blade, and reducing the temperature of the wall surface of the leading edge of the blade.
As a specific implementation manner, it needs to be further explained in this implementation manner that the cross section of the tapered hole is an elliptical structure. The bell mouth of oval structure conveniently processes equally, the internal face does not have any edges and corners structure, when air conditioning got into the bell mouth of oval structure in, can not produce extra stress, and the great one end in aperture of the bell mouth of oval structure was given vent to anger as it and is held, the less one end in aperture was regarded as its inlet end, the inlet end of the bell mouth of oval structure and the end intercommunication of giving vent to anger of first through-hole mutually, on the basis of guaranteeing that gas stable circulation and gas film hole give vent to anger and hold the grow, make processing more convenient.
As a specific implementation manner, it should be further explained in this implementation manner that the first through hole is a circular through hole with a circular cross section, where the cross section is preferably a cross section passing through a middle point of a central axis of the first through hole 1, and a portion at two ends of the first through hole 1 is avoided to be an inclined surface. Circular through-hole processing is convenient, and the internal wall does not have any edges and corners structure, when air conditioning gets into in the first through-hole of circular through-hole form, can not produce extra stress.
As a specific implementation manner, it should be further described in this implementation manner that the cross section of the first through hole is an elliptical structure, where the cross section is preferably a cross section passing through a midpoint of a central axis of the first through hole, and a portion of two ends of the first through hole is avoided to be an inclined surface. The first through hole of oval structure processing is convenient, and the internal face does not have any edges and corners structure, when air conditioning got into in the first through hole of oval structure, can not produce extra stress.
As a specific implementation manner, it needs to be further explained in this implementation manner that the inner wall surface of the first through hole includes a plurality of first planes and a plurality of transition curved surfaces, any two first planes are connected by one transition curved surface, and each first plane is tangent to the transition curved surfaces on both sides of the first plane, and at this time, the radian of each transition curved surface is 45 °, and this implementation manner can also achieve an effect that the inner wall surface does not have any corner structure, and when cold air enters the first through hole of the elliptical structure, no additional stress is generated.
As a specific implementation manner, it needs to be further explained in this implementation manner that the first through hole is provided with a first complete circular tangent plane and a second complete circular tangent plane, one point on the first complete circular tangent plane coincides with one point on the hole edge of the air inlet end of the first through hole, that is, the first complete circular tangent plane passes through and only passes through one point on the hole edge of the air inlet end of the first through hole, one point on the second complete circular tangent plane coincides with one point on the hole edge of the air outlet end of the first through hole, that is, the second complete circular tangent plane passes through and only passes through one point on the hole edge of the air outlet end of the first through hole, and the axes of the first through hole are perpendicular to the first complete circular tangent plane and the second complete circular tangent plane, so as to ensure that the part of the first complete circular tangent plane and the second complete circular tangent plane cut on the first through hole corresponds to the hole plane of the first through hole, that when the first through hole is circular, the parts of the first complete round section and the second complete round section, which are cut on the first through hole, are circular corresponding to the first through hole, when the first through hole is oval, the parts of the first complete round section and the second complete round section, which are cut on the first through hole, are oval corresponding to the first through hole, and at the moment, the distance between the first complete round section and the second complete round section is not less than 0.3mm, so that the flow of cooling air can be effectively controlled.
Has the advantages that: according to the utility model, the air film hole formed by combining the first through hole and the conical hole is adopted, a better cooling air film can be formed on the front edge of the blade, the first through hole realizes the control of the cooling air flow, the conical hole increases the area of the outlet of the air film hole, the speed of cooling air at the outlet of the air film hole is reduced, the covering effect of the cooling air flow is improved, the cooling effect of the blade is obviously improved, the temperature of the wall surface of the front edge of the blade is reduced, the sharp edge of the outlet edge of the air film hole is passivated, the stress concentration coefficient of the outlet edge of the air film hole is improved, the stress of the outlet edge of the air film hole is reduced, the temperature of the wall surface of the blade is reduced, the reliability of the blade is improved, and the service life of the blade is prolonged; the utility model has simple structure, good manufacturability, high application value and wide application prospect.
Drawings
FIG. 1 is a schematic view of the leading edge portion of a turbine blade with composite structure film holes therein according to the present invention;
FIG. 2 is a schematic sectional view of a gas film hole of a composite structure according to the present invention.
Reference numerals: 1-a first via; 2-a tapered hole; 3-turbine blades.
Detailed Description
The first embodiment is as follows:
as shown in fig. 1 and fig. 2, in order to improve the film cooling effect of the leading edge of the turbine rotor blade and solve the problem of the film cooling of the cylindrical film hole of the leading edge of the blade, the present embodiment provides a composite structure film hole for cooling the leading edge of the turbine blade, which includes a first through hole 1 and a tapered hole 2 sequentially connected from the inlet direction to the outlet direction, the first through hole 1 and the tapered hole 2 are combined into the composite structure film hole, and penetrate through the leading edge of the turbine blade 3, wherein the first through hole 1 and the tapered hole 2 are not coaxially arranged, a better cooling film can be formed on the leading edge of the turbine blade 3, the cooling effect of the turbine blade 3 is significantly improved, the wall temperature of the leading edge of the turbine blade 3 is reduced, the cross-sectional area of the outlet of the tapered hole 2 is larger than the area of the cross-section of the first through hole 1, where the cross-section of the first through hole 1 is preferably a cross-section passing through the midpoint of the central axis of the first through hole 1, the outlet with a larger point can passivate an acute angle at the edge of the air outlet of the film hole with the combined structure, reduce the stress of the hole wall and protect the turbine blade 3, thereby prolonging the service life of the turbine blade; the axial lead of the first through hole 1 is a straight line, so that the first through hole 1 is a through hole which is communicated with the bottom and is not a bent hole, the manufacturing process difficulty and possible stress concentration generated when the bent hole is adopted are avoided, and the turbine blade 3 is well protected; the inner wall surface of the first through hole 1 and the inner wall surface of the conical hole 2 have no edges, so that the gas passing through the gas film hole with the combined structure does not have unnecessary edges in the first through hole 1 and the conical hole 2 to generate stress. It should be noted that, in normal operation, the cooling air enters from the bottom of the turbine blade, passes through the inner cavity of the turbine blade, enters the first through hole 1, and then circulates out from the tapered hole 2.
According to the air film hole, the first through hole 1 and the conical hole 2 are combined to form a good cooling air film on the front edge of the blade, the first through hole 1 controls the flow of cooling air, the conical hole 2 increases the area of an outlet of the air film hole, the speed of the cooling air at the outlet of the air film hole is reduced, the covering effect of the cooling air flow is improved, the cooling effect of the blade is obviously improved, the temperature of the wall surface of the front edge of the blade is reduced, the sharp edge of the outlet edge of the air film hole is passivated, the stress concentration coefficient of the outlet edge of the air film hole is improved, the stress of the outlet edge of the air film hole is reduced, the temperature of the wall surface of the blade is reduced, the reliability of the blade is improved, and the service life of the blade is prolonged; the application has the advantages of simple structure, good manufacturability, high application value and wide application prospect.
As a specific implementation manner, it needs to be further explained in this implementation manner that the tapered hole 2 is a conical hole with a circular cross section. Conical hole facilitates the processing, and the internal face does not have any edges and corners structure, when air conditioning got into conical hole 2 in, can not produce extra stress, and the great one end in aperture in conical hole was regarded as its end of giving vent to anger, and the less one end in aperture is regarded as its inlet end, and the inlet end in conical hole communicates with the end of giving vent to anger of first through-hole 1 mutually, on the basis of guaranteeing that gaseous stable circulation and gas film hole give vent to anger the end grow for processing is more convenient.
As a specific implementation manner, it should be further explained in this implementation manner that the first through hole 1 is a circular through hole with a circular cross section, where the cross section of the first through hole 1 is preferably a cross section passing through a middle point of a central axis of the first through hole 1, and portions at two ends of the first through hole 1 are avoided to be an inclined surface. Circular through-hole processing is convenient, and the internal wall does not have any edges and corners structure, when air conditioning gets into circular through-hole form first through-hole 1 in, can not produce extra stress.
Example two:
the present embodiment is a further improvement on the basis of the first embodiment, and specific differences between the present embodiment and the first embodiment are as follows:
as a specific embodiment, it should be further explained in this embodiment that the taper angle of the tapered hole 2 is not less than 10 °, specifically may be 10 °, 30 °, 50 °, 70 °, 80 °, or 110 °, and the taper angle of the tapered hole 2 is less than 120 °, so as long as the taper angle of the tapered hole 2 is within a range of greater than or equal to 10 ° and less than 120 °, which may be determined according to practical situations and is not specifically limited, and the diameter of the air outlet may be increased within the same length, so as to meet the requirement that the diameter of the air outlet of the tapered hole 2 is greater than the diameter of the first through hole 1, thereby forming a better cooling air film at the leading edge of the blade, significantly improving the cooling effect of the blade, and reducing the temperature of the wall surface of the leading edge of the blade.
Example three:
the present embodiment is a further improvement on the basis of the first embodiment, and specific differences between the present embodiment and the first embodiment are as follows:
as a specific implementation manner, it should be further explained in this implementation manner that, unlike the first implementation example, the cross section of the tapered hole 2 is an elliptical structure. The bell mouth 2 of oval structure conveniently processes equally, the internal face does not have any edges and corners structure, when air conditioning got into the bell mouth 2 of oval structure in, can not produce extra stress, and the great one end in aperture of the bell mouth 2 of oval structure gives vent to anger as it and holds, the less one end in aperture is as its inlet end, the inlet end of the bell mouth 2 of oval structure communicates with the end of giving vent to anger of first through-hole 1 mutually, on the basis of guaranteeing that gas stable circulation and air film hole give vent to anger and hold the grow, make processing more convenient.
Example four:
the present embodiment is a further improvement made on the basis of any one of the first to third embodiments, and the specific differences between the present embodiment and any one of the first to third embodiments are as follows:
as a specific implementation manner, it should be further described in this implementation manner that, unlike any one of the first to third implementation examples, the cross section of the first through hole 1 is an elliptical structure, where the cross section is preferably a cross section passing through a midpoint of a central axis of the first through hole 1, and portions at two ends of the first through hole 1 are avoided to be an inclined surface. The first through hole 1 of the oval structure is convenient to process, the inner wall surface does not have any corner structure, and when cold air enters the first through hole 1 of the oval structure, extra stress cannot be generated.
Example five:
the present embodiment is a further improvement made on the basis of any one of the first to third embodiments, and the specific differences between the present embodiment and any one of the first to third embodiments are as follows:
as a specific implementation manner, it needs to be further described in this implementation manner that, unlike any one of the first to third embodiments, an inner wall surface of the first through hole 1 includes a plurality of first planes and a plurality of transition curved surfaces, any two first planes are connected by one transition curved surface, and each first plane is tangent to the transition curved surfaces on both sides of the first plane, and at this time, the radian of each transition curved surface is 45 °, so that the implementation manner can also achieve an effect that no edge structure is provided on the inner wall surface, and when cold air enters the first through hole 1 having an elliptical structure, no additional stress is generated.
As a specific implementation manner, it needs to be further explained in this implementation manner that the first through hole 1 is provided with a first complete circular tangent plane 101 and a second complete circular tangent plane 102, one point on the first complete circular tangent plane 101 coincides with one point on the hole edge of the air inlet end of the first through hole 1, that is, the first complete circular tangent plane 101 passes through and only passes through one point on the hole edge of the air inlet end of the first through hole 1, one point on the second complete circular tangent plane 102 coincides with one point on the hole edge of the air outlet end of the first through hole 1, that is, the second complete circular tangent plane 102 passes through and only passes through one point on the hole edge of the air outlet end of the first through hole 1, and the axes of the first through hole 1 are both perpendicular to the first complete circular tangent plane 101 and the second complete circular tangent plane 102, so as to ensure that the cut portions of the first complete circular tangent plane 101 and the second complete circular tangent plane 102 on the first through hole 1 correspond to the hole surface of the first through hole 1, that is to say, when the first through hole 1 is circular, the cut part of the first complete circular section 101 and the second complete circular section 102 on the first through hole 1 is circular corresponding to the first through hole 1, when the first through hole 1 is oval, the cut part of the first complete circular section 101 and the second complete circular section 102 on the first through hole 1 is oval corresponding to the first through hole 1, at this time, the distance between the first complete circular section 101 and the second complete circular section 102 is not less than 0.3mm, so that the cooling air flow rate can be effectively controlled.
Finally, it should be noted that: the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The composite structure air film hole for cooling the leading edge of the turbine blade is characterized by comprising a first through hole (1) and a tapered hole (2) which are sequentially communicated from an inlet direction to an outlet direction, wherein the first through hole (1) and the tapered hole (2) are arranged in a non-coaxial mode, and the cross section area of the outlet of the tapered hole (2) is larger than that of the cross section of the first through hole (1); the axial lead of the first through hole (1) is a straight line; the inner wall surface of the first through hole (1) and the inner wall surface of the conical hole (2) have no edges and corners.
2. A composite structural film hole for turbine blade leading edge cooling as claimed in claim 1 wherein said tapered hole (2) is a conical hole of circular configuration in cross section.
3. A composite structural film hole for turbine blade leading edge cooling as claimed in claim 1 wherein the taper angle of the tapered hole (2) is not less than 10 °.
4. A composite structural film hole for turbine blade leading edge cooling as claimed in claim 1 wherein the cross section of the tapered hole (2) is an elliptical configuration.
5. A composite structural film hole for turbine blade leading edge cooling according to claim 1 wherein said first through hole (1) is a circular through hole having a circular configuration in cross section.
6. A composite structural film hole for turbine blade leading edge cooling according to claim 1 wherein the cross-section of the first through hole (1) is an elliptical configuration.
7. The composite structure film hole for cooling the leading edge of the turbine blade is characterized in that the inner wall surface of the first through hole (1) comprises a plurality of first planes and a plurality of transition curved surfaces, any two first planes are connected through one transition curved surface, and each first plane is tangent to the transition curved surfaces on two sides of the first plane.
8. A composite structure film hole for cooling the leading edge of a turbine blade according to any one of claims 1-7, wherein the first through hole (1) is provided with a first complete circular section (101) and a second complete circular section (102), one point on the first complete circular section (101) coincides with one point on the hole edge of the air inlet end of the first through hole (1), one point on the second complete circular section (102) coincides with one point on the hole edge of the air outlet end of the first through hole (1), and the axes of the first through holes (1) are perpendicular to the first complete circular section (101) and the second complete circular section (102), and the distance between the first complete circular section (101) and the second complete circular section (102) is not less than 0.3 mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110508216.9A CN112922677A (en) | 2021-05-11 | 2021-05-11 | Combined structure air film hole for cooling front edge of turbine blade |
| CN2021105082169 | 2021-05-11 |
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| CN216043898U true CN216043898U (en) | 2022-03-15 |
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| CN202110508216.9A Pending CN112922677A (en) | 2021-05-11 | 2021-05-11 | Combined structure air film hole for cooling front edge of turbine blade |
| CN202122506651.6U Active CN216043898U (en) | 2021-05-11 | 2021-10-18 | Combined structure air film hole for cooling front edge of turbine blade |
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| CN202110508216.9A Pending CN112922677A (en) | 2021-05-11 | 2021-05-11 | Combined structure air film hole for cooling front edge of turbine blade |
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| CN114034489B (en) * | 2022-01-10 | 2022-03-25 | 成都中科翼能科技有限公司 | Gas turbine engine ground starting acceleration time calculation method |
| CN114876582B (en) * | 2022-06-28 | 2023-05-16 | 西北工业大学 | Turbine blade and aeroengine |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2227965B (en) * | 1988-10-12 | 1993-02-10 | Rolls Royce Plc | Apparatus for drilling a shaped hole in a workpiece |
| JPH07279612A (en) * | 1994-04-14 | 1995-10-27 | Mitsubishi Heavy Ind Ltd | Heavy oil burning gas turbine cooling blade |
| US5779437A (en) * | 1996-10-31 | 1998-07-14 | Pratt & Whitney Canada Inc. | Cooling passages for airfoil leading edge |
| US6918742B2 (en) * | 2002-09-05 | 2005-07-19 | Siemens Westinghouse Power Corporation | Combustion turbine with airfoil having multi-section diffusion cooling holes and methods of making same |
| US7887294B1 (en) * | 2006-10-13 | 2011-02-15 | Florida Turbine Technologies, Inc. | Turbine airfoil with continuous curved diffusion film holes |
| US20090169394A1 (en) * | 2007-12-28 | 2009-07-02 | General Electric Company | Method of forming cooling holes and turbine airfoil with hybrid-formed cooling holes |
| EP2990605A1 (en) * | 2014-08-26 | 2016-03-02 | Siemens Aktiengesellschaft | Turbine blade |
| KR101853550B1 (en) * | 2016-08-22 | 2018-04-30 | 두산중공업 주식회사 | Gas Turbine Blade |
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