Method of assembling a gas turbine engine

摘要

A method of assembling a seal in a horizontal split plane gas turbine engine including providing a rotor assembly including a turbine blade assembly defining a forward face and a seal ring extending axially from the forward face. The rotor assembly is positioned extending through a lower compressor casing and a lower turbine casing, the positioning including tilting the rotor assembly at an angle relative to the longitudinal axis for the engine. An upper turbine casing is positioned over the tilted rotor assembly, and the upper and lower turbine casings define a circumferentially extending seal groove. The rotor assembly is moved in an axially forward direction to position the seal ring in axially overlapping relation within the seal groove. The longitudinal axis of the rotor assembly is then aligned with the longitudinal axis of the turbine engine to further position the seal ring within the seal groove.

主权项

1. A method of assembling a seal in a split plane gas turbine engine having a compressor section, a turbine section and a rotor assembly extending through said compressor section and said turbine section, said rotor assembly supporting a compressor blade assembly and a turbine blade assembly, and including a lower compressor casing and a lower turbine casing axially aligned along a horizontal longitudinal axis of said turbine engine during said assembling of said seal, said longitudinal axis defining a rotational axis of said rotor assembly during operation of said gas turbine engine, the method comprising:
i) providing a seal ring extending axially from a forward face of said turbine blade assembly; ii) positioning said rotor assembly in association with said lower compressor casing and said lower turbine casing, said positioning including tilting said rotor assembly such that a longitudinal axis of said rotor assembly is at a predetermined angle relative to said longitudinal axis of said turbine engine and such that said compressor blade assembly is maintained at an elevated position relative to said turbine blade assembly; iii) positioning an upper turbine casing in engagement with said lower turbine casing and over the tilted rotor assembly, said lower turbine casing and said upper turbine casing including a circumferentially extending seal groove defining an axially facing cavity for receiving said seal ring, and said seal ring having an initial non-overlapping position in relation to said seal groove; iv) moving said rotor assembly in an axial direction toward said compressor section while maintaining said rotor assembly tilted at said predetermined angle to position said seal ring in axially overlapping relation within said seal groove; and v) further positioning said rotor assembly such that said longitudinal axis of said rotor assembly coincides with said longitudinal axis of said turbine engine, for effecting a further axial movement of an upper portion of said seal ring into said seal groove, said further positioning said rotor assembly including another tilting of said rotor assembly in which said longitudinal axis of said rotor assembly is tilted an opposite and equal amount to the tilting at the predetermined angle of step ii).