BR0200352A - Conjunto de invólucro e método de usinagem do mesmo - Google Patents

Conjunto de invólucro e método de usinagem do mesmo

Info

Publication number
BR0200352A
BR0200352A BR0200352-0A BR0200352A BR0200352A BR 0200352 A BR0200352 A BR 0200352A BR 0200352 A BR0200352 A BR 0200352A BR 0200352 A BR0200352 A BR 0200352A
Authority
BR
Brazil
Prior art keywords
housing assembly
machined
flight
machining
rotor blades
Prior art date
Application number
BR0200352-0A
Other languages
English (en)
Other versions
BR0200352B1 (pt
Inventor
Jonathan James Stow
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of BR0200352A publication Critical patent/BR0200352A/pt
Publication of BR0200352B1 publication Critical patent/BR0200352B1/pt

Links

Classifications

    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49236—Fluid pump or compressor making
    • Y10T29/4924—Scroll or peristaltic type
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49295—Push rod or rocker arm making

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)

Abstract

"CONJUNTO DE INVóLUCRO E MéTODO DE USINAGEM DO MESMO". Método de usinagem de uma superfície interna (56) de um conjunto de invólucro (42) que se estende, em geral, circunferencialmente em torno de um eixo central (18) de um motor de avião de turbina a gás (10). O método inclui a determinação de folgas radiais pré-usinadas (60) durante o vóo entre as pontas (26) das pás de rotor (20) no motor (10) e a superfície interna (56) do conjunto de invólucro (42) em cada uma de uma pluralidade de localizações circunferencialmente espaçadas em torno do conjunto de invólucro (42). A superfície interna (56) do conjunto de invólucro (42) é usinada com base nas folgas radiais pré-usinadas (60) para proporcionar uma folga radial pós-usinada geralmente uniforme (60), durante o vóo, entre as pontas (26) das pás de rotor (20) e a superfície interna (56) do conjunto de invólucro (42) em cada uma das localizações circunferencialmente espaçadas em torno do conjunto de invólucro (42).
BRPI0200352-0A 2001-02-16 2002-02-14 conjunto de invàlucro e mÉtodo de usinagem do mesmo. BR0200352B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/785,765 US6409471B1 (en) 2001-02-16 2001-02-16 Shroud assembly and method of machining same

Publications (2)

Publication Number Publication Date
BR0200352A true BR0200352A (pt) 2002-10-08
BR0200352B1 BR0200352B1 (pt) 2010-12-14

Family

ID=25136566

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0200352-0A BR0200352B1 (pt) 2001-02-16 2002-02-14 conjunto de invàlucro e mÉtodo de usinagem do mesmo.

Country Status (6)

Country Link
US (1) US6409471B1 (pt)
EP (1) EP1233148B1 (pt)
JP (1) JP4156246B2 (pt)
BR (1) BR0200352B1 (pt)
CA (1) CA2370219C (pt)
SG (1) SG98475A1 (pt)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4698847B2 (ja) * 2001-01-19 2011-06-08 三菱重工業株式会社 ガスタービン分割環
US6906808B2 (en) * 2002-05-30 2005-06-14 General Electric Company Methods and apparatus for measuring a surface contour of an object
US6931751B2 (en) * 2002-08-28 2005-08-23 General Electric Company Methods and apparatus for securing components for inspection
US6842995B2 (en) * 2002-10-09 2005-01-18 General Electric Company Methods and apparatus for aligning components for inspection
US6886422B2 (en) * 2002-10-09 2005-05-03 General Electric Co. Methods and apparatus for inspecting components
US6890150B2 (en) * 2003-08-12 2005-05-10 General Electric Company Center-located cutter teeth on shrouded turbine blades
ITMI20041781A1 (it) 2004-09-17 2004-12-17 Nuovo Pignone Spa Dispositivo di protezione per uno statore di una turbina
US7207771B2 (en) * 2004-10-15 2007-04-24 Pratt & Whitney Canada Corp. Turbine shroud segment seal
JP4764219B2 (ja) * 2006-03-17 2011-08-31 三菱重工業株式会社 ガスタービンのシール構造
CA2653346A1 (en) * 2006-06-01 2007-12-06 Igeacare Systems, Inc. Remote health care system with treatment verification
US7871244B2 (en) * 2007-02-15 2011-01-18 Siemens Energy, Inc. Ring seal for a turbine engine
EP2141328A1 (en) * 2008-07-03 2010-01-06 Siemens Aktiengesellschaft Sealing system between a shroud segment and a rotor blade tip and manufacturing method for such a segment
EP2189630A1 (de) * 2008-11-19 2010-05-26 Siemens Aktiengesellschaft Gasturbine, Leitschaufelträger für eine solche Gasturbine und Gas- bzw. Dampfturbinenanlage mit einer solchen Gasturbine
US20120177484A1 (en) * 2011-01-07 2012-07-12 General Electric Company Elliptical Sealing System
US20140321993A1 (en) * 2011-01-07 2014-10-30 General Electric Company Elliptical sealing system
US9874218B2 (en) 2011-07-22 2018-01-23 Hamilton Sundstrand Corporation Minimal-acoustic-impact inlet cooling flow
US9833869B2 (en) * 2013-02-11 2017-12-05 United Technologies Corporation Blade outer air seal surface
FR3002273B1 (fr) * 2013-02-20 2017-06-23 Snecma Dispositif avionique pour la surveillance d'une turbomachine
GB201309580D0 (en) 2013-05-29 2013-07-10 Siemens Ag Rotor tip clearance
EP3078448B1 (en) * 2015-04-10 2018-07-11 Rolls-Royce Deutschland Ltd & Co KG Method for machining a casing for a turbo engine.
US11428241B2 (en) * 2016-04-22 2022-08-30 Raytheon Technologies Corporation System for an improved stator assembly
EP3434864B1 (en) * 2017-07-27 2020-12-16 General Electric Company A method and system for repairing a turbomachine

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2740192C2 (de) 1977-09-07 1981-11-12 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Spaltdichtung für eine um ihre Längsachse verstellbare, axial umströmte Leitschaufel einer Strömungsmaschine
US4363599A (en) 1979-10-31 1982-12-14 General Electric Company Clearance control
US4767272A (en) 1987-10-14 1988-08-30 United Technologies Corporation Method for reducing blade tip variation of a bladed rotor
US4999991A (en) 1989-10-12 1991-03-19 United Technologies Corporation Synthesized feedback for gas turbine clearance control
US5054997A (en) * 1989-11-22 1991-10-08 General Electric Company Blade tip clearance control apparatus using bellcrank mechanism
US5281085A (en) * 1990-12-21 1994-01-25 General Electric Company Clearance control system for separately expanding or contracting individual portions of an annular shroud
GB9103809D0 (en) 1991-02-23 1991-04-10 Rolls Royce Plc Blade tip clearance control apparatus
US5212940A (en) * 1991-04-16 1993-05-25 General Electric Company Tip clearance control apparatus and method
US5462403A (en) * 1994-03-21 1995-10-31 United Technologies Corporation Compressor stator vane assembly
US5439348A (en) 1994-03-30 1995-08-08 United Technologies Corporation Turbine shroud segment including a coating layer having varying thickness
US5639210A (en) * 1995-10-23 1997-06-17 United Technologies Corporation Rotor blade outer tip seal apparatus
US5667358A (en) 1995-11-30 1997-09-16 Westinghouse Electric Corporation Method for reducing steady state rotor blade tip clearance in a land-based gas turbine to improve efficiency
GB2313414B (en) 1996-05-24 2000-05-17 Rolls Royce Plc Gas turbine engine blade tip clearance control
US6467339B1 (en) 2000-07-13 2002-10-22 United Technologies Corporation Method for deploying shroud segments in a turbine engine

Also Published As

Publication number Publication date
CA2370219A1 (en) 2002-08-16
BR0200352B1 (pt) 2010-12-14
EP1233148A3 (en) 2005-09-14
SG98475A1 (en) 2003-09-19
US6409471B1 (en) 2002-06-25
EP1233148B1 (en) 2012-10-17
CA2370219C (en) 2009-06-09
JP2002256812A (ja) 2002-09-11
JP4156246B2 (ja) 2008-09-24
EP1233148A2 (en) 2002-08-21

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Legal Events

Date Code Title Description
B06A Patent application procedure suspended [chapter 6.1 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 14/02/2002, OBSERVADAS AS CONDICOES LEGAIS.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time

Free format text: REFERENTE A 13A ANUIDADE.

B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)

Free format text: EM VIRTUDE DA EXTINCAO PUBLICADA NA RPI 2308 DE 31-03-2015 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDA A EXTINCAO DA PATENTE E SEUS CERTIFICADOS, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.