SEAL ASSEMBLY FOR A GAS TURBINE ENGINE WITH REDUCED PRESSURE LOAD ARRANGEMENT
A seal assembly (60) for a gas turbine engine (20) includes, a seal arc segment (66), a sealing portion (72), a first rail (74R-1) and a second rail (74R-2) opposed to the first rail. The sealing portion extends in a circumferential direction between opposed mate faces in an axial direction between...
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Main Authors | , , , , |
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Format | Patent |
Language | English French German |
Published |
08.11.2023
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Subjects | |
Online Access | Get full text |
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Summary: | A seal assembly (60) for a gas turbine engine (20) includes, a seal arc segment (66), a sealing portion (72), a first rail (74R-1) and a second rail (74R-2) opposed to the first rail. The sealing portion extends in a circumferential direction between opposed mate faces in an axial direction between a leading edge (72LE) and a trailing edge (72TE). Each of the first and second rails extend outwardly in a radial direction from the sealing portion (72) to respective first and second edge faces (74RF-1, 74RF-2), and the sealing portion (72) has a sealing face (72A) dimensioned to bound a gas path (GP) and includes a backside face (72C) opposed to the sealing face. Each of the first and second rails includes at least one interface bore (74B) dimensioned to receive a retention pin (84). |
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Bibliography: | Application Number: EP20210156979 |