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COMPRESSOR OUTLET GUIDE VANE STRUCTURE

IP.com Disclosure Number: IPCOM000245440D
Publication Date: 2016-Mar-10
Document File: 7 page(s) / 52K

Publishing Venue

The IP.com Prior Art Database

Abstract

[0001] In a gas turbine engine, an integral outlet guide vane ("OGV")-diffuser structure removes tangential swirl from compressor discharge air, decreases flow Mach number suitable for combustion and serves as structural member to carry nozzle axial and torque loads. The outlet guide vane assembly includes a plurality of circumferentially spaced guide vanes extending radially across the flow path between outer and inner annular end walls. Inner and outer OGV support arms are attached to the end walls such that a line of action is straight and it passes through the midchord of the OGVs. This reduces OGV stresses thereby increasing durability.

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ABSTRACT


[0001] In a gas turbine engine, an integral outlet guide vane ("OGV")-diffuser structure removes tangential swirl from compressor discharge air, decreases flow Mach number suitable for combustion and serves as structural member to carry nozzle axial and torque loads. The outlet guide vane assembly includes a plurality of circumferentially spaced guide vanes extending radially across the flow path between outer and inner annular end walls. Inner and outer OGV support arms are attached to the end walls such that a line of action is straight and it passes through the midchord of the OGVs. This reduces OGV stresses thereby increasing durability.

BACKGROUND


[0002] This disclosure relates generally to gas turbine engines and more particularly to outlet guide vanes and diffusers located downstream of the compressor of such engines.


[0003] In a gas turbine engine, an integral OGV-diffuser structure removes tangential swirl from compressor discharge air, decreases flow Mach number suitable for combustion and serves as structural member to carry nozzle axial and torque loads. The OGV assembly includes a plurality of circumferentially spaced guide vanes extending radially across the flow path between outer and inner annular end walls. In operation of the engine, a very large axial plug load is applied to the OGV assembly. In addition, the flowing combustion gases exert a substantial torque on the downstream turbine nozzle guide vanes about the engine axis. This torque and the axial force resulting from the pressure drop is transferred to the outer case through and consequently through the OGVs, resulting in higher OGV stresses. In conjunction with high stresses, high flow path temperatures on the OGVs results in higher creep and lowered low cycle fatigue ("LCF") life. Described herein is a configuration for reducing OGV stresses.

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COMPRESSOR OUTLET GUIDE VANE STRUCTURE


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BRIEF DESCRIPTION OF THE DRAWINGS


[0004] The concept may be best understood by reference to the following description taken in conjunction with the accompanying drawing figures, in which:


[0005] FIG. 1 is a schematic cross-sectional view of a gas turbine engine;


[0006] FIG. 2 is a schematic cross-sectional view of an outlet guide vane and diffuser of a turbofan engine; and


[0007] FIG. 3 is a schematic cross-sectional view taken along lines 3-3 of FIG. 2.

DETAILED DESCRIPTION OF THE CONCEPT


[0008] Illustrated in FIG. 1 is a schematic representation of a gas turbine engine 10 including in serial flow communication about an axial centerline axis 12 conventional annular and axisymmetric structures including an axial flow compressor 14, combustor 16, high pressure turbine nozzle 18, and high pressure turbine ("HPT") 20. The compressor 14 receives inlet airflow 22 and compresses it. The compression generates relatively hot compressed airflow 24 which is flowed through OGV assembly 36 to the combustor 16 in which it is conventionally mixed wi...