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Variable turbine nozzle system

一种涡轮机、喷嘴的技术，应用在涡轮/推进装置的冷却、机械设备、发动机元件等方向，能够解决人力和涡轮机停机时间昂贵、不适合等问题

Inactive Publication Date: 2012-05-16
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this design may also be unsuitable for prolonged field operations, and periodic overhauls are expensive in both manpower and turbine downtime

Method used

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Examples

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Embodiment Construction

[0060] At least one embodiment of the invention is described below with reference to its application in relation to the operation of a turbomachine. Although embodiments of the invention are described with respect to a turbine in the form of a gas turbine, it should be understood that the teachings are equally applicable to other turbines, including but not limited to other types of turbines or compressors. Additionally, at least one embodiment of the invention is described below with reference to nominal dimensions and including a set of nominal dimensions. However, it should be apparent to a person skilled in the art that the invention is equally applicable to any suitable turbine and / or compressor. Furthermore, it should be apparent to those skilled in the art that the present invention is equally applicable to nominal dimensions and / or various ratios of nominal dimensions.

[0061] As indicated above, aspects of the invention provide nozzles and turbines including nozzles...

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PUM

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Abstract

A nozzle (120) is disclosed for use in a turbine (12) or compressor. In an embodiment, each of a plurality of vanes (122) is supported by an outer shroud including a plurality of outer shroud segments (124) disposed adjacent to adjoining segments (144) in end-to-end relationship. Each segment (144) includes a hole (146) therethrough, dimensioned to receive a vane extension sleeve (148). This system may be used in conjunction with a modulated cooling system and may allow for improved removal for overhaul.

Description

technical field [0001] The present disclosure generally relates to turbine technology. More specifically, the present disclosure relates to variable area nozzles for use in multi-stage turbines. Background technique [0002] In the design of a gas turbine engine, fluid flow through the engine is varied by a plurality of stator vanes and rotor blades. Typically, stationary nozzle segments direct a flow of working fluid into a stage of turbine blades connected to a rotating rotor. Each nozzle has an airfoil or vane shape configured such that when a set of nozzles is positioned around a rotor of a turbine, they direct airflow in an optimal direction and at an optimal pressure against the rotor blades. [0003] Direction and pressure requirements may change as operating conditions, including temperature, engine mass flow, etc. change. Stationary vanes do not provide optimal direction and pressure for the full range of operating conditions, resulting in reduced efficiency and / ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04F02C7/16
CPCF01D9/04F01D17/162
Inventor A·J·G·克雷斯波R·W·夸恩D·R·约翰斯G·C·利奥塔
Owner GENERAL ELECTRIC CO
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