Seal assembly for a guide vane assembly
First Claim
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1. A guide vane assembly for a gas turbine engine comprising:
- a first airfoil, including a first airfoil trailing edge;
a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween; and
a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge, wherein the seal assembly comprises;
a pressure component; and
a seal, including a protruding side and a buried side, wherein the pressure component is in contact with the buried side and the pressure component is configured to maintain contact between the protruding side and at least one of the first airfoil trailing edge and the second airfoil leading edge.
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Abstract
The present disclosure relates generally to a guide vane assembly including a first airfoil, including a first airfoil trailing edge, a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween, and a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge.
18 Citations
13 Claims
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1. A guide vane assembly for a gas turbine engine comprising:
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a first airfoil, including a first airfoil trailing edge; a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween; and a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge, wherein the seal assembly comprises; a pressure component; and a seal, including a protruding side and a buried side, wherein the pressure component is in contact with the buried side and the pressure component is configured to maintain contact between the protruding side and at least one of the first airfoil trailing edge and the second airfoil leading edge. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A gas turbine engine comprising:
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a compressor section; a plurality of guide vane assemblies, positioned within the compressor section, wherein each guide vane assembly comprising; a first airfoil, including a first airfoil trailing edge, and a first airfoil trailing edge longitudinal axis; a second airfoil, including a second airfoil leading edge, and a second airfoil leading edge longitudinal axis, wherein the second airfoil leading edge is positioned aft the first airfoil trailing edge to create a gap therebetween; a slot disposed within the first airfoil trailing edge positioned substantially parallel to the first airfoil trailing edge longitudinal axis; and a seal assembly disposed within the slot to engage the second airfoil leading edge, wherein the seal assembly comprises; a pressure component; and a seal, including a protruding side and a buried side, wherein the pressure component is in contact with the buried side and the pressure component is configured to maintain contact between the protruding side and the first airfoil trailing edge.
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13. A gas turbine engine comprising:
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a compressor section; a plurality of guide vane assemblies, positioned within the compressor section, wherein each guide vane assembly comprising; a first airfoil, including a first airfoil trailing edge, and a first airfoil trailing edge longitudinal axis; a second airfoil, including a second airfoil leading edge, and a second airfoil leading edge longitudinal axis, wherein the second airfoil leading edge is positioned aft the first airfoil trailing edge to create a gap therebetween; a slot disposed within the second airfoil leading edge positioned substantially parallel to the second airfoil leading edge longitudinal axis; and a seal assembly disposed within the slot to engage the first airfoil trailing edge, wherein the seal assembly comprises; a pressure component; and a seal, including a protruding side and a buried side, wherein the pressure component is in contact with the buried side and the pressure component is configured to maintain contact between the protruding side and the second airfoil leading edge.
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Specification