Turbine shroud segment with buffer air seal system
First Claim
1. A turbine shroud segment adapted for use in a gas turbine engine having a central axis about which primary components of the engine rotate, the turbine shroud segment comprisinga carrier segment comprising metallic materials, the carrier segment includes a mount plate and a plurality of receiving walls that extend inwardly in a radial direction from the mount plate toward the central axis to define an attachment-receiving space,a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around the central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space channel formed by the carrier segment, anda seal member that extends radially between the receiving walls of the carrier segment and the runner of the blade track segment to resist the movement of gasses into the attachment-receiving space,wherein at least one of the receiving walls included in the carrier segment is formed to include buffer air passageways configured to discharge buffer air along the seal member to resist the movement of gasses into the attachment-receiving space,wherein the plurality of receiving walls are formed to include a seal channel that extends outwardly in the radial direction and the seal channel receives the seal member, andwherein the seal channel formed by the receiving walls extends all the way around the attachment portion of the blade track segment.
4 Assignments
0 Petitions
Accused Products
Abstract
A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
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Citations
20 Claims
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1. A turbine shroud segment adapted for use in a gas turbine engine having a central axis about which primary components of the engine rotate, the turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment includes a mount plate and a plurality of receiving walls that extend inwardly in a radial direction from the mount plate toward the central axis to define an attachment-receiving space, a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around the central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space channel formed by the carrier segment, and a seal member that extends radially between the receiving walls of the carrier segment and the runner of the blade track segment to resist the movement of gasses into the attachment-receiving space, wherein at least one of the receiving walls included in the carrier segment is formed to include buffer air passageways configured to discharge buffer air along the seal member to resist the movement of gasses into the attachment-receiving space, wherein the plurality of receiving walls are formed to include a seal channel that extends outwardly in the radial direction and the seal channel receives the seal member, and wherein the seal channel formed by the receiving walls extends all the way around the attachment portion of the blade track segment.
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11. A turbine shroud segment adapted for use in a gas turbine engine having a central axis about which primary components of the engine rotate, the turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment including a mount plate and a wall that extends inwardly in a radial direction from the mount plate toward the central axis, a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around the central axis, and a seal member that extends radially between the wall of the carrier segment and the runner of the blade track segment to resist the movement of gasses between the wall of the carrier segment and the runner of the blade track segment, wherein the wall included in the carrier segment is formed to include a plurality of buffer air passageways configured to discharge buffer air along the interface of the carrier segment and the seal member, wherein the wall of the carrier segment is formed to include a buffer groove that extends outwardly in the radial direction, wherein the buffer groove is arranged radially outward of at least a portion of the seal member, and wherein the buffer air passageways are located to discharge buffer air into the buffer groove, and wherein the wall is formed to include a seal channel that receives the seal member, the buffer groove is smaller than the seal channel, and the buffer groove extends outward in the radial direction from the seal channel.
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13. A turbine shroud segment adapted for use in a gas turbine engine having a central axis about which primary components of the engine rotate, the turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment including a mount plate and a wall that extends inwardly in a radial direction from the mount plate toward the central axis, a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around the central axis, and a seal member that extends radially between the wall of the carrier segment and the runner of the blade track segment to resist the movement of gasses between the wall of the carrier segment and the runner of the blade track segment, wherein the wall included in the carrier segment is formed to include a plurality of buffer air passageways configured to discharge buffer air along the interface of the carrier segment and the seal member, wherein the wall of the carrier segment is formed to include a buffer groove that extends outwardly in the radial direction, wherein the buffer groove is arranged radially outward of at least a portion of the seal member, and wherein the buffer air passageways are located to discharge buffer air into the buffer groove, and wherein the wall of the carrier segment is formed to include at least one buffer dam that extends into a buffer groove and the buffer dam is sized to restrict the flow of buffer air along the buffer groove so that different portions of the buffer groove are pressurized at different levels when buffer air is supplied to the buffer groove from the buffer air passageways.
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19. A turbine shroud segment adapted for use in a gas turbine engine having a central axis about which primary components of the engine rotate, the turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment including a mount plate and a wall that extends inwardly in a radial direction from the mount plate toward the central axis, a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around the central axis, and a seal member that extends radially between the wall of the carrier segment and the runner of the blade track segment to resist the movement of gasses between the wall of the carrier segment and the runner of the blade track segment, wherein the wall included in the carrier segment is formed to include a plurality of buffer air passageways configured to discharge buffer air along the interface of the carrier segment and the seal member, wherein the seal member is formed to include a plurality of bleed holes adapted to conduct buffer air through the seal member, and wherein the plurality of bleed holes are formed only along a leading edge of the blade track segment.
Specification