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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Bibliographic Details
Main Authors ARBONA, Jaime A, BLEIL, Justin K, KEENE, Andrew D, THILL, Carson A. Roy, MAHONEY, Danielle
Format Patent
LanguageEnglish
French
German
Published 08.11.2023
Subjects
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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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).
Bibliography:Application Number: EP20210156979