Turbine airfoil with metering plates for refresher holes
First Claim
1. A gas turbine engine hollow airfoil comprising:
- an airfoil outer wall having widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base to a radially outer airfoil tip, a cooling circuit within said airfoil said cooling circuit having radially extending first, middle, and last channels arranged respectively in series, said first channel in fluid communication with a source of cooling air from outside said airfoil, said last channel in fluid communication with one of said edges, a refresher passageway extending through a radially inner wall bounding a radially inner portion of said last channel and in fluid communication with said source of cooling air, and said refresher passageway is separate, spaced apart, and independent from said first channel.
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Accused Products
Abstract
A gas turbine engine hollow airfoil has an airfoil outer wall with widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of the airfoil and extending radially from a radially inner base to a radially outer airfoil tip. A cooling circuit within the airfoil has radially extending first, middle, and last channels arranged respectively in series with the first channel in fluid communication with a source of cooling air from outside the airfoil. The last channel is in fluid communication with one of the edges. A refresher passageway extends through a radially inner wall bounding a radially inner portion of the last channel and is in fluid communication with the source of cooling air. The refresher passageway is separate, spaced apart, and independent from the first channel. In one embodiment, a metering plate covers an inlet to the refresher passageway and the metering plate has a metering hole over the inlet and the metering hole is adjustable. The hollow airfoil may be part of a gas turbine engine blade extending radially outwardly from a root with the first channel extending through the root and having an entrance at a bottom surface of the root. The refresher passageway extends through a radially inner wall bounding a radially inner portion of the last channel and through the root and the inlet to the refresher passageway is located at the bottom surface of the root and is separate and spaced apart from the entrance of the first channel. The metering plate is disposed on the bottom surface of the root.
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Citations
28 Claims
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1. A gas turbine engine hollow airfoil comprising:
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an airfoil outer wall having widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base to a radially outer airfoil tip, a cooling circuit within said airfoil said cooling circuit having radially extending first, middle, and last channels arranged respectively in series, said first channel in fluid communication with a source of cooling air from outside said airfoil, said last channel in fluid communication with one of said edges, a refresher passageway extending through a radially inner wall bounding a radially inner portion of said last channel and in fluid communication with said source of cooling air, and said refresher passageway is separate, spaced apart, and independent from said first channel. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A gas turbine engine blade comprising:
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a hollow airfoil extending radially outwardly from a root;
said airfoil comprising an airfoil outer wall having widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base at said root to a radially outer airfoil tip, a cooling circuit within said airfoil, said cooling circuit having radially extending first, middle, and last channels arranged respectively in series, said first channel extending through said root and having an entrance at a bottom surface of said root, said last channel in fluid communication with one of said edges, a refresher passageway extending through a radially inner wall bounding a radially inner portion of said last channel and through said root, and said refresher passageway having an inlet at said bottom surface of said root, said inlet being separate and spaced apart from said entrance. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18, 20, 21, 22, 23, 24, 25, 26, 27, 28)
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19. A gas turbine engine blade comprising:
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a hollow airfoil extending radially outwardly from a root;
said airfoil comprising an airfoil outer wall having widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base at said root to a radially outer airfoil tip, a forward flowing serpentine cooling circuit and an aft flowing serpentine cooling circuit within said airfoil, said cooling circuits each having radially extending first, middle, and last channels arranged respectively in series, each of said first channels extending through said root and having an entrance at a bottom surface of said root, said last channel of said forward flowing serpentine cooling circuit in fluid communication with said leading edge, said last channel of said aft flowing serpentine cooling circuit in fluid communication with said trailing edge, forward and aft refresher passageways extending through forward and aft radially inner walls bounding radially inner portions of said forward and aft last channels, respectively, and through said root, and said refresher passageways having inlets at said bottom surface of said root, said inlets being separate and spaced apart from said entrances.
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Specification