Gas turbine engine systems involving mechanically alterable vane throat areas
First Claim
Patent Images
1. A vane for a gas turbine engine comprising:
- a leading edge;
a trailing edge;
a suction side surface extending between the leading edge and the trailing edge;
a cavity having an aperture located in the suction side surface;
a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture; and
a fluidic jet having an outlet port operative to emit gas into a gas flow path located adjacent to the suction side surface.
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Abstract
Gas turbine engine systems involving mechanically alterable vane throat areas are provided. In this regard, a representative vane for a gas turbine engine includes: a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in the suction side surface; and a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture.
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Citations
20 Claims
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1. A vane for a gas turbine engine comprising:
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a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in the suction side surface; a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture; and a fluidic jet having an outlet port operative to emit gas into a gas flow path located adjacent to the suction side surface. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A vane assembly for a gas turbine engine comprising:
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a vane having a pressure side; and an adjacent vane having a suction side located adjacent to the pressure side, the vane and the adjacent vane defining a throat area therebetween, the suction side of the adjacent vane having a cavity and a barrel retained by the cavity, the barrel being moveable such that movement of the barrel alters the throat area. - View Dependent Claims (12, 13, 14, 15, 16, 17)
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18. A gas turbine engine comprising:
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a vane assembly having a vane and an adjacent vane; the vane having a pressure side; and the adjacent vane having a suction side located adjacent to the pressure side, the vane and the adjacent vane defining a throat area therebetween, the suction side of the adjacent vane having a cavity and a barrel retained by the cavity, the barrel being moveable such that movement of the barrel alters the throat area. - View Dependent Claims (19, 20)
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Specification