Turbine vane with removable platform inserts
First Claim
Patent Images
1. A turbine vane assembly comprising:
- an airfoil having a first end region and a second end region;
a first platform operatively connected to the first end region of the airfoil, the first platform having a gas path face, the first platform including a first platform frame having a receptacle therein, the receptacle opening to at least the gas path face; and
an insert removably retained in the receptacle, wherein the gas path face is defined at least in part by the first platform frame and the insert, wherein a plurality of passages extend through the first platform frame and into fluid communication with the receptacle, whereby a coolant can be supplied to the insert and/or the receptacle.
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Abstract
Aspects of the invention are related to a turbine vane assembly in which at least one of the platforms is equipped with one or more removable platform inserts. The inserts can be used in those areas of the platform where failures or damage has been known to occur, among other locations. If an insert becomes damaged or is destroyed during engine operation, the insert can be easily replaced, and the platform frames and the airfoil can be reused. As a result, the overall life of the vane can be extended. Further, the inserts can be made of materials that can reduce cooling requirements compared to known turbine vanes, thereby allowing cooling air to be used for other uses in the engine.
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Citations
21 Claims
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1. A turbine vane assembly comprising:
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an airfoil having a first end region and a second end region; a first platform operatively connected to the first end region of the airfoil, the first platform having a gas path face, the first platform including a first platform frame having a receptacle therein, the receptacle opening to at least the gas path face; and an insert removably retained in the receptacle, wherein the gas path face is defined at least in part by the first platform frame and the insert, wherein a plurality of passages extend through the first platform frame and into fluid communication with the receptacle, whereby a coolant can be supplied to the insert and/or the receptacle. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A turbine vane assembly comprising:
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an airfoil having a first end region and a second end region; a first platform operatively connected to the first end region of the airfoil, the first platform having a gas path face, the first platform including a first platform frame having at least one receptacle therein, each of the receptacles opening to at least the gas path face, and at least one insert, each of the at least one inserts being removably retained in one of the receptacles, wherein the insert is associated entirely with the first platform and forms no portion of the airfoil, wherein the insert is made of a material having a lower heat resistance than the material of the first platform frame, wherein the gas path face is defined at least in part by the first platform frame and the at least one insert. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19)
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20. A method of repairing a damaged turbine vane comprising the steps of:
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(a) providing a turbine vane assembly that includes; an airfoil having a first end region and a second end region; a first platform operatively connected to the first end region of the airfoil, the first platform having a gas path face, the first platform including a first platform frame having a receptacle therein, the receptacle opening to at least the gas path face; and an insert removably retained in the receptacle, wherein the gas path face is defined at least in part by the first platform frame and the insert, wherein the insert is associated entirely with the first platform and forms no portion of the airfoil, wherein the insert is damaged; (b) removing the damaged insert; and (c) placing an undamaged insert into the receptacle so that the undamaged insert is retained therein.
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21. A turbine vane assembly comprising:
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an airfoil having a first end region and a second end region; a first platform operatively connected to the first end region of the airfoil, the first platform having a gas path face and an associated thickness, the first platform having a first circumferential side and a second circumferential side, the first platform including a first platform frame having a recess therein, the recess opening to the gas path face and one of the circumferential sides, wherein the recess does not extend through the entire thickness of the first platform; and an insert being received and removably retained in the receptacle, wherein the gas path face is partially defined by the insert and wherein one of the circumferential sides is partially defined by the insert, wherein the insert is associated entirely with the first platform and forms no portion of the airfoil, whereby the insert is inserted and removed from the recess through the recess opening in the circumferential side of the first platform.
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Specification