TURBINE AIRFOIL VANE WITH AN IMPINGEMENT INSERT HAVING A PLURALITY OF IMPINGEMENT NOZZLES
A turbine airfoil vane usable in a turbine engine and including at least one cooling system with an impingement plate having one or more impingement nozzles is disclosed. The turbine vane impingement nozzles may extend towards an outer wall forming the turbine vane and may reduce the mixing of cooling fluids and impingement jets found in conventional configurations. Instead, the nozzles terminate within close proximity of the outer wall, thereby reducing the effect of cooling fluid cross flow.
This invention is directed generally to turbine airfoil vanes, and more particularly to hollow turbine airfoil vanes having an impingement insert for passing fluids, such as air, to cool the airfoils.
BACKGROUNDTypically, gas turbine engines include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power. Combustors often operate at high temperatures that may exceed 2,500 degrees Fahrenheit. Typical turbine combustor configurations expose turbine vane and blade assemblies to these high temperatures. As a result, turbine vanes and blades must be made of materials capable of withstanding such high temperatures. In addition, turbine vanes and blades often contain cooling systems for prolonging the life of the vanes and blades and reducing the likelihood of failure as a result of excessive temperatures.
Typically, turbine vanes are formed from an elongated portion forming a vane having one end configured to be coupled to a vane carrier and an opposite end configured to be movably coupled to an inner endwall. The vane is ordinarily composed of a leading edge, a trailing edge, a suction side, and a pressure side. The inner aspects of most turbine vanes typically contain an intricate maze of cooling circuits forming a cooling system. The cooling circuits in the vanes receive air from the compressor of the turbine engine and pass the air through the ends of the vane adapted to be coupled to the vane carrier. The cooling circuits often include multiple flow paths that are designed to maintain all aspects of the turbine vane at a relatively uniform temperature. At least some of the air passing through these cooling circuits is exhausted through orifices in the leading edge, trailing edge, suction side, and pressure side of the vane.
The cooling system, as shown in
This invention relates to a turbine airfoil vane usable in a turbine engine. The turbine vane may include one or more cooling systems with an impingement plate having one or more impingement nozzles. The turbine vane impingement nozzles may extend towards an outer wall forming the turbine vane and may reduce the mixing of cooling fluids with impingement jets. Instead, the nozzles may terminate within close proximity of the outer wall, thereby reducing the effect of cooling fluid cross flow.
The turbine vane may include a generally elongated hollow airfoil formed from an outer wall. The vane may include a leading edge, a trailing edge, a pressure side, a suction side, an outer endwall at a first end, an inner endwall at a second end opposite the first end, and a cooling system positioned within the generally elongated airfoil. The cooling system may include one or more impingement inserts positioned in internal aspects of a central cooling chamber of the cooling system. The impingement insert directs cooling fluids towards the outer wall forming the generally elongated airfoil to impinge upon the inner surface of the outer wall and cool the outer wall. The impingement insert may include a plurality of impingement nozzles extending toward an inner surface of the outer wall from an impingement plate, wherein each nozzle includes at least one impingement orifice. Each nozzle may include one or more impingement orifices positioned at an outermost aspect of the nozzle for directing cooling fluids orthogonally away from the impingement plate.
The impingement nozzles may be positioned such that a distance between the one or more impingement orifices and the inner surface of the outer wall may be less than a conventional distance between a conventional impingement plate with holes and an outer wall of a conventional vane. In addition, a distance between the impingement plate and the inner surface of the outer wall may be greater than a conventional distance between the conventional impingement plate with holes and the outer wall of the conventional vane.
One or more of the impingement nozzles may generally cylindrical, and in at least one embodiment, a plurality of the impingement nozzles may generally cylindrical. One or more of the impingement nozzles may be generally conical, and in at least one embodiment, a plurality of impingement nozzles may be generally conical. The impingement nozzles may have any one of a number of different shapes. In particular, the impingement nozzles may have a cross-sectional shape formed from a cylinder, a rectangle, a triangle or a semicircle.
An advantage of this invention is that the impingement jets are emitted from the impingement plate through impingement nozzles closer to the outer wall forming the turbine vane without reducing the cross-sectional area of the channel formed between the outer wall and the impingement plate.
Another advantage of this invention is that the impingement jets are discharged through the impingement plate in close proximity to the outer wall such that cooling fluid cross flow is not sufficient to disrupt the impingement jets.
These and other embodiments are described in more detail below.
The accompanying drawings, which are incorporated in and form a part of the specification, illustrate embodiments of the presently disclosed invention and, together with the description, disclose the principles of the invention.
As shown in
The cooling system 12 may be configured to cool internal and external aspects of the turbine vane 10 usable in a turbine engine. In at least one embodiment, the turbine airfoil cooling system 12 may be configured to be included within a stationary turbine vane 10, as shown in
As shown in
As shown in
In at least one embodiment, one or more impingement nozzles 16 may be generally cylindrical. As such, a plurality of impingement nozzles 16 may be generally cylindrical. In other embodiments, one or more impingement nozzles 16 may have a cross-sectional area formed as a cylinder, a rectangle, a triangle, a semicircle, and other appropriate shapes. The impingement nozzles 16 may also be configured with a conical shape such that a cross-sectional area at a base 58 is greater than a cross-sectional area at the outermost aspect 56. One or a plurality of impingement nozzles 16 may be configured have a generally conical shape and may include one or more impingement orifices 54.
The impingement nozzles 16 may be aligned into rows, as shown in
The impingement orifices 54 may extend from the impingement plate 14 a distance 64 that is less than a conventional distance 8 between a conventional impingement plate 2 with holes 4 and an outer wall 6 of a conventional vane, as shown in
As shown in
The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention.
Claims
1. A turbine vane, comprising:
- a generally elongated hollow airfoil formed from an outer wall, and having a leading edge, a trailing edge, a pressure side, a suction side, an outer endwall at a first end, an inner endwall at a second end opposite the first end, and a cooling system positioned within the generally elongated airfoil; and
- at least one impingement insert positioned in internal aspects of a central cooling chamber of the cooling system;
- wherein the impingement insert includes a plurality of impingement nozzles extending toward an inner surface of the outer wall from an impingement plate, wherein each nozzle includes at least one impingement orifice.
2. The turbine vane of claim 1, wherein a distance between the at least one impingement orifice and the inner surface of the outer wall is less than a conventional distance between a conventional impingement plate with holes and an outer wall of a conventional vane.
3. The turbine vane of claim 2, wherein a distance between the impingement plate and the inner surface of the outer wall is greater than a conventional distance between the conventional impingement plate with holes and the outer wall of the conventional vane.
4. The turbine vane of claim 1, wherein at least one of the impingement nozzles is generally cylindrical.
5. The turbine vane of claim 4, wherein the plurality of impingement nozzles are generally cylindrical.
6. The turbine vane of claim 1, wherein at least one of the impingement nozzles is generally conical.
7. The turbine vane of claim 6, wherein the plurality of impingement nozzles are generally conical.
8. The turbine vane of claim 1, wherein each nozzle includes at least one impingement orifice positioned at an outermost aspect of the nozzle for directing cooling fluids orthogonally away from the impingement plate.
9. The turbine vane of claim 1, wherein at least one of the plurality of nozzles has a cross-sectional area selected from the group consisting of a cylinder, a rectangle, a triangle and a semicircle.
10. A turbine vane, comprising:
- a generally elongated hollow airfoil formed from an outer wall, and having a leading edge, a trailing edge, a pressure side, a suction side, an outer endwall at a first end, an inner endwall at a second end opposite the first end, and a cooling system positioned within the generally elongated airfoil; and
- at least one impingement insert positioned in internal aspects of a central cooling chamber of the cooling system;
- wherein the impingement insert includes a plurality of impingement nozzles extending toward an inner surface of the outer wall from an impingement plate, wherein each nozzle includes at least one impingement orifice;
- wherein a distance between the at least one impingement orifice and the inner surface of the outer wall is less than a conventional distance between a conventional impingement plate with holes and an outer wall of a conventional vane;
- wherein a distance between the impingement plate and the inner surface of the outer wall is greater than a conventional distance between the conventional impingement plate with holes and the outer wall of the conventional vane.
11. The turbine vane of claim 10, wherein at least one of the impingement nozzles is generally cylindrical.
12. The turbine vane of claim 11, wherein the plurality of impingement nozzles are generally cylindrical.
13. The turbine vane of claim 10, wherein at least one of the impingement nozzles is generally conical.
14. The turbine vane of claim 13, wherein the plurality of impingement nozzles are generally conical.
15. The turbine vane of claim 10, wherein each nozzle includes at least one impingement orifice positioned at an outermost aspect of the nozzle for directing cooling fluids orthogonally away from the impingement plate.
16. The turbine vane of claim 10, wherein at least one of the plurality of nozzles has a cross-sectional area selected from the group consisting of a cylinder, a rectangle, a triangle and a semicircle.
17. A turbine vane, comprising:
- a generally elongated hollow airfoil formed from an outer wall, and having a leading edge, a trailing edge, a pressure side, a suction side, an outer endwall at a first end, an inner endwall at a second end opposite the first end, and a cooling system positioned within the generally elongated airfoil; and
- at least one impingement insert positioned in internal aspects of a central cooling chamber of the cooling system;
- wherein the impingement insert includes a plurality of impingement nozzles extending toward an inner surface of the outer wall from an impingement plate, wherein each nozzle includes at least one impingement orifice;
- wherein a distance between the at least one impingement orifice and the inner surface of the outer wall is less than a conventional distance between a conventional impingement plate with holes and an outer wall of a conventional vane;
- wherein a distance between the impingement plate and the inner surface of the outer wall is greater than a conventional distance between the conventional impingement plate with holes and the outer wall of the conventional vane;
- wherein each nozzle includes at least one impingement orifice positioned at an outermost aspect of the nozzle for directing cooling fluids orthogonally away from the impingement plate.
18. The turbine vane of claim 17, wherein at least one of the plurality of nozzles has a cross-sectional area selected from the group consisting of a cylinder, a rectangle, a triangle and a semicircle.
19. The turbine vane of claim 17, wherein the plurality of impingement nozzles are generally cylindrical.
20. The turbine vane of claim 17, wherein the plurality of impingement nozzles are generally conical.
Type: Application
Filed: Sep 20, 2010
Publication Date: Mar 22, 2012
Inventor: Ching-Pang Lee (Cincinnati, OH)
Application Number: 12/885,740
International Classification: F01D 5/18 (20060101);