General Electric Company

Andrew Shepherd

Richard William Albrecht, Jr

Robert J Corsmeier

Robert J Hemmelgarn

A turbine nozzle support assembly includes nozzle segments each having an inner band with an integral retention flange extending radially inwardly therefrom. A plurality of retention tabs extend radially inwardly and are spaced axially aft of the retention flange to define a capture slot therebetween. A nozzle support includes a radially outwardly extending upper flange having a plurality of support pins extending axially, forwardly therefrom and disposed in complementary retention apertures in the retention flanges of the nozzle segments. A retention key is disposed in the capture slot axially between the upper flange and the retention tabs for axially retaining the nozzle segments on the nozzle support.

Turbine nozzle support assembly

A high pressure turbine in a gas turbine engine contains an arrangement of channels, holes and windows through components controlling the operating clearance between tips of turbine blades and casing shroud segments wherein the arrangement defines a serial supply path for a single cooling airflow through the clearance control components. The arrangement also includes a plurality of holes defined through a cover located between shroud holders and segments.

Arrangement for defining improved cooling airflow supply path through

In a gas turbine engine having an annular casing with a stationary support structure, a high pressure turbine, and an annular high pressure turbine nozzle having at least one stage which includes a plurality of circumferentially aligned nozzle segments and which is disposed in the annular casing between a combustor and the high pressure turbine, a nozzle support arrangement is provided for mounting each nozzle segment to the stationary support structure. The arrangement includes a single mounting pin mounted on and extending from an annular nozzle support flange on the casing support structure and a hole defined in an oval shape in the one end portion of an inner band flange for receiving the mounting pin in an interference fitting relation. The oval-shaped hole has a greater height than width such that a tight tangential fit of the pin with the hole is provided along the width of the hole and a loose fit of the pin with the hole is provided along the height of the hole so as to ensure negligible variation of the tangential location of the nozzle segments relative to one another and to the support structure, while allowing free axial rocking of the nozzle segment on the inner band without bending the pin nor the support flange.

Turbine nozzle support arrangement

A gas turbine engine nozzle includes outer and inner bands and a plurality of spaced apart vanes extending therebetween. The inner band includes an outer surface facing the outer band over which is flowable combustion gases, and a radially inwardly facing inner surface. A plurality of circumferentially spaced apart turbulators are joined to the inner band inner surface adjacent the trailing edges of the vanes for increasing cooling of the inner band by cooling air channeled over the turbulators.

Gas turbine engine nozzle

A nozzle seal arrangement, for a turbine nozzle of a gas turbine engine, which impedes leakage of high pressure cooling air past the nozzle inner bands into the flow path to the outside thereof. The nozzle seal arrangement includes an annular nozzle support flange attached to and extending along the stationary support structure adjacent to the nozzle, a band flange attached to and extending along the inner band of each nozzle segment and disposed adjacent to the support flange, a continuous seal member having a W-shaped configuration in cross-section which extends circumferentially about the central axis, and an annular recess defined in the forward face of the nozzle support flange which extends circumferentially about the central axis and receives and seats the seal member at the aft side thereof.

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Fairfield, OH, United States of America

Andrew Shepherd