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ANNULAR SEALING ASSEMBLY

IP.com Disclosure Number: IPCOM000250493D
Publication Date: 2017-Jul-25
Document File: 6 page(s) / 47K

Publishing Venue

The IP.com Prior Art Database

Abstract

Aspects of the disclosure described herein are directed to an annular sealing assembly. For purposes of illustration, the present disclosure will be described with respect to a free turbine engine. It will be understood, however, that aspects of the disclosure described herein are not so limited and that the annular sealing assembly as described herein can be implemented in other turbine engines, including but not limited to turbojet, turboprop, turboshaft, and turbofan engines. Aspects of the disclosure discussed herein may have general applicability within in non-aircraft engines having an annular sealing assembly for a combustor such as other mobile applications and non-mobile industrial, commercial, and residential applications.

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Annular Sealing Assembly

BACKGROUND

[1]                     Turbine engines are driven by a flow of air and combusted gases passing through the engine onto a multitude of rotating turbine blades. 

[2]                     A combustor can be provided within the engine used to combust the gases to exhaust the gas through the turbine section. The combustor is fluidly coupled with a turbine at an interface having an annular seal. Cooling and integrity of the annular seal is required.

DRAWINGS

[3]                     In the drawings:

[4]                     FIG. 1 is an enlarged cross-sectional view of a reverse flow combustor.

[5]                     FIG. 2 is an enlarged cross-sectional view of an annular seal at an interface between the reverse flow combustor and a turbine nozzle.

DESCRIPTION

[6]                     Aspects of the disclosure described herein are directed to an annular sealing assembly. For purposes of illustration, the present disclosure will be described with respect to a free turbine engine. It will be understood, however, that aspects of the disclosure described herein are not so limited and that the annular sealing assembly as described herein can be implemented in other turbine engines, including but not limited to turbojet, turboprop, turboshaft, and turbofan engines. Aspects of the disclosure discussed herein may have general applicability within in non-aircraft engines having an annular sealing assembly for a combustor such as other mobile applications and non-mobile industrial, commercial, and residential applications.

[7]                     As used herein, the term “forward” or “upstream” refers to moving in a direction toward the engine inlet, or a component being relatively closer to the engine inlet as compared to another component. The term “aft” or “downstream” used in conjunction with “forward” or “upstream” refers to a direction toward the rear or outlet of the engine or being relatively closer to the engine outlet as compared to another component. Additionally, as used herein, the terms “radial” or “radially” refer to a dimension extending between a center longitudinal axis of the engine and an outer engine circumference. Furthermore, as used herein, the term “set” or a “set” of elements can be any number of elements, including only one.

[8]                     All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, aft, etc.) are only used for identification purposes to aid the reader’s understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of aspects of the disclosure described herein. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and can include intermediate members between a collection of elements and relative movement between elements unless otherwise indicated. As such, connection references do not necessarily infe...