MX168121B - Mejoras en diafragma de compresor - Google Patents

Mejoras en diafragma de compresor

Info

Publication number
MX168121B
MX168121B MX019596A MX1959690A MX168121B MX 168121 B MX168121 B MX 168121B MX 019596 A MX019596 A MX 019596A MX 1959690 A MX1959690 A MX 1959690A MX 168121 B MX168121 B MX 168121B
Authority
MX
Mexico
Prior art keywords
casing
planes
section
cross
diaphragm
Prior art date
Application number
MX019596A
Other languages
English (en)
Inventor
Augustine Joseph Scalzo
Original Assignee
Westinghouse Electric Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Publication of MX168121B publication Critical patent/MX168121B/es

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La presente invención se refiere a mejoras en diafragma de compresor para una turbina de gas, que tiene una carcasa, un rotor que incluye, una pluralidad de aspas rotatorias dispuestas en sentido axial a lo largo de un eje que tiene una pluralidad de discos; dicha carcasa tiene ranuras de una primera sección transversal predeterminada formadas en sentido circunferencial en la carcasa del compresor de la turbina; el diafragma está sostenido e incluye una pluralidad de planos aerodinámicos de álabes, cada uno con una cubierta interna y una cubierta externa integrales; la cubierta externa incluye una parte superior de una sección transversal complementaria con la primera sección transversal predeterminada para poder recibirlas en forma deslizable en las ranuras de la carcasa de la turbina, caracterizadas porque las barras de conexión están dispuestas en ranuras formadas en dichas cubiertas externas y cubiertas internas, y se extienden a través de la pluralidad de planos aerodinámicos contiguos y los interconectan en sus respectivas cubiertas adyacentes, internas y externas, para transferir carga entre planos adyacentes.
MX019596A 1989-02-21 1990-02-21 Mejoras en diafragma de compresor MX168121B (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/312,287 US5022818A (en) 1989-02-21 1989-02-21 Compressor diaphragm assembly

Publications (1)

Publication Number Publication Date
MX168121B true MX168121B (es) 1993-05-04

Family

ID=23210757

Family Applications (1)

Application Number Title Priority Date Filing Date
MX019596A MX168121B (es) 1989-02-21 1990-02-21 Mejoras en diafragma de compresor

Country Status (9)

Country Link
US (1) US5022818A (es)
EP (1) EP0384166B1 (es)
JP (1) JP2628604B2 (es)
KR (1) KR0152441B1 (es)
AR (1) AR243011A1 (es)
AU (1) AU621444B2 (es)
CA (1) CA2010446A1 (es)
DE (1) DE69005845T2 (es)
MX (1) MX168121B (es)

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US8894370B2 (en) * 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
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EP2204547B1 (fr) * 2008-12-29 2013-12-11 Techspace Aero Virole extérieure et procédé de montage par soudage entre cette virole et une aube fixe
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JP6271077B2 (ja) * 2014-07-24 2018-01-31 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ ガスタービンエンジン内で使用可能なステータベーンシステム
US20180112546A1 (en) * 2015-03-17 2018-04-26 SIEMENS AKTIENGESELLSCHAFTü Stator vane dampening system usable within a turbine engine
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FR3048719B1 (fr) * 2016-03-14 2018-03-02 Safran Aircraft Engines Redresseur de flux pour turbomachine avec plateformes integrees et rapportees
KR101953462B1 (ko) * 2017-05-24 2019-02-28 두산중공업 주식회사 베인 어셈블리를갖는 가스터빈
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CN114278580B (zh) * 2021-12-21 2023-07-28 江苏航天水力设备有限公司 一种可更换导叶的大型贯流泵
CN114962338B (zh) * 2022-04-27 2024-04-12 四川航天中天动力装备有限责任公司 一种涡喷发动机的分体式静子机匣结构及其装配方法

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Also Published As

Publication number Publication date
US5022818A (en) 1991-06-11
JPH02245403A (ja) 1990-10-01
AR243011A1 (es) 1993-06-30
AU621444B2 (en) 1992-03-12
EP0384166A3 (en) 1990-12-05
CA2010446A1 (en) 1990-08-21
KR0152441B1 (ko) 1998-11-02
DE69005845D1 (de) 1994-02-24
EP0384166A2 (en) 1990-08-29
KR900013213A (ko) 1990-09-05
DE69005845T2 (de) 1994-05-05
JP2628604B2 (ja) 1997-07-09
EP0384166B1 (en) 1994-01-12
AU4900790A (en) 1990-08-30

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