Device for sealing gas turbine stator blades
First Claim
1. A sealing device for a gas turbine stator blade, in which air is guided from air holes formed in a blade ring through a space formed by said blade ring, a heat insulating ring and an outer shroud, the air being further guided from said space through a seal tube in the stator blade into an inner shroud, such that a pressure in a cavity of said inner shroud may be maintained at a higher pressure than that in a combustion gas passage to seal the interior of said inner shroud,wherein said air holes include a first air hole communicating with said space, and a second air hole communicating with said seal tube.
1 Assignment
0 Petitions
Accused Products
Abstract
A sealing device for a gas turbine stator blade, in which an outer shroud (32) is mounted by heat insulating rings (32a,32b) on a blade ring (50). The blade ring (50) has a first air hole (1), which communicates with a space (53), and a second air hole (51), which communicates with a seal tube (2). The seal tube (2) is inserted into the second air hole (51), and a spring (6) is arranged between a projection (4) of the tube (2) and a retaining portion (5) of the air hole (51) to removably secure the seal tube (2). Cooling air (54) flows through the first air hole (1) to cool the shrouds and the inside of a stator blade (31) until it is released from the trailing edge of the blade. The cooling air also flows into a cavity (36) so that a high pressure can be maintained without a pressure loss because the tube (2) is independent of the space (53) in the blade ring.
92 Citations
13 Claims
-
1. A sealing device for a gas turbine stator blade, in which air is guided from air holes formed in a blade ring through a space formed by said blade ring, a heat insulating ring and an outer shroud, the air being further guided from said space through a seal tube in the stator blade into an inner shroud, such that a pressure in a cavity of said inner shroud may be maintained at a higher pressure than that in a combustion gas passage to seal the interior of said inner shroud,
wherein said air holes include a first air hole communicating with said space, and a second air hole communicating with said seal tube.
-
8. A stator blade sealing arrangement for a gas turbine, said sealing arrangement comprising:
-
a stator blade having an outer shroud and an inner shroud;
a blade ring connected to said outer shroud, said blade ring including a first air hole and a second air hole;
heat insulating rings connecting said blade ring with said outer shroud;
a radial space defined by said heat insulating rings, said outer shroud, and said blade ring, wherein said first air hole communicates with said radial space;
a seal tube extending from said second air hole, through said radial space and said stator blade and into said inner shroud, said seal tube having a first end communicating with said second air hole, wherein air bled from a compressor can be guided into said radial space, via said first air hole, and into an interior of said inner shroud through said seal tube, via said second air hole, so that pressure in a cavity of said inner shroud can be maintained at a higher pressure than a pressure in a combustion gas passage. - View Dependent Claims (9, 10, 11, 12, 13)
-
Specification