EP2746540A2 - Ensemble de carter de compresseur donnant accès à un ensemble d'étanchéité d'aubes de compresseur - Google Patents

Ensemble de carter de compresseur donnant accès à un ensemble d'étanchéité d'aubes de compresseur Download PDF

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Publication number
EP2746540A2
EP2746540A2 EP13197076.6A EP13197076A EP2746540A2 EP 2746540 A2 EP2746540 A2 EP 2746540A2 EP 13197076 A EP13197076 A EP 13197076A EP 2746540 A2 EP2746540 A2 EP 2746540A2
Authority
EP
European Patent Office
Prior art keywords
assembly
casing
seal
removable cover
compressor casing
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
EP13197076.6A
Other languages
German (de)
English (en)
Other versions
EP2746540A3 (fr
Inventor
Sanji Ekanayake
Alston Ilford Scipio
Joseph P. Rizzo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2746540A2 publication Critical patent/EP2746540A2/fr
Publication of EP2746540A3 publication Critical patent/EP2746540A3/fr
Withdrawn legal-status Critical Current

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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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings

Definitions

  • the subject matter disclosed herein relates generally to turbine engine components and, more specifically, to compressor casing assemblies.
  • Turbine engines operate according to well-known principles wherein an incoming stream of atmospheric air flows through the engine along an axially-extending flow path.
  • at least a portion of the incoming air is compressed in a compressor section of the engine and is then mixed with fuel and ignited in a combustor section to produce a high-energy, high-temperature exhaust gas stream.
  • the hot gas stream exits the combustor and is channeled through a turbine section that extracts energy from the exhaust stream to power the compressor and to provide useful work, such as powering an aircraft in flight or producing electricity.
  • At least some turbines use a sealing element along the inner surface of the casing, to reduce leakage between the blade tips and the casing.
  • Various sealing techniques have been used.
  • known sealing elements lose effectiveness over time and may require replacement.
  • the disclosure provides a solution to the problem of having to remove the midcompressor casing of a turbine engine in order to access the zero stage seal assembly of the compressor.
  • the invention relates to a compressor casing assembly.
  • the compressor casing assembly includes a forward compressor casing; a removable cover and a seal assembly.
  • the compressor casing assembly also includes a midcompressor casing having a cavity adapted to receive the seal assembly, and a cover groove adapted to receive a removable cover that secures the seal assembly.
  • a turbine engine having a midcompressor casing having a face surface and an inner surface, the compressor casing having a cavity formed on the inner surface and a groove formed on the face surface.
  • the turbine engine also includes a plurality of arcuate seal segments configured to be inserted into the cavity, and a removable cover disposed in contact with the arcuate seal segments and being removably secured to the midcompressor casing.
  • an assembly having a midcompressor casing having a face surface and an inner surface, the inner surface having a cavity and the face surface having a cover groove.
  • the assembly includes a plurality of arcuate seal segments configured to be inserted into the cavity.
  • the assembly also includes a removable cover adapted to be inserted into the cover groove, the removable cover is disposed in contact with at least some of the plurality of arcuate seal segments and secured to the compressor casing.
  • the embodiments disclosed herein provide for easy access to a zero stage seal assembly without removal of a midcompressor casing. This is accomplished with a removable cover that is secured to the midcompressor casing that serves to hold the zero stage seal assembly in place. Removal of the removable cover provides access to the zero stage seal assembly.
  • Fig. 1 is a cross-sectional view of a turbine engine 11 taken through a longitudinal axis 12 extending through the turbine engine 11.
  • turbine engine 11 also includes a compressor 13 having a plurality of rotor blades 15 that are circumferentially spaced and that extend radially outward towards a midcompressor casing 17 from a rotor wheel 19 which collectively form the rotor shaft.
  • Stator vanes 20 are positioned adjacent to each set of rotor blades 15, and in combination form one of a plurality of stages 21.
  • Stator vanes 20 are securely coupled to midcompressor casing 17 and extend radially inward to interface with rotor wheel 19.
  • Each of the plurality of stages 21 directs a flow of compressed air through compressor 13.
  • Rotor blades 15 are circumscribed by midcompressor casing 17, such that an annular gap (not shown in Fig. 1 ) is defined between midcompressor casing 17 and a rotor blade tip 23 of each of the rotor blades 15.
  • Each gap is sized to facilitate minimizing a quantity of compressed air that bypasses the rotor blades 15.
  • a seal assembly 25 is used between midcompressor casing 17 and rotor 26 to substantially seal the gap defined therebetween.
  • seal assembly 25 facilitates reducing bypass flow of compressed air between midcompressor casing 17 and rotor blade tip 23.
  • compressor 13 includes eighteen separate stages 21.
  • seal assembly 25 as described herein may be employed in any suitable type of compressor with any number of stages.
  • An inlet guide vane (IGV 27) is positioned upstream form the rotor blades 15. IGV 27 directs the airflow onto the rotor blades 15.
  • FIG. 2 Illustrated in Figure 2 is an enlarged view of the detail area 29 shown in Figure 1 illustrating a casing assembly 31.
  • Casing assembly 31 is disposed adjacent to IGV 27, zero stage rotor 35 and zero stage stator 37.
  • Zero stage seal assembly 39 is disposed adjacent to zero stage rotor 35.
  • Casing assembly 31 includes a midcompressor casing 17 and a forward compressor casing 22. Midcompressor casing 17 and forward compressor casing 22 are fastened by means of casing fastener(s) 41.
  • Casing assembly 31 also includes a removable cover 43 disposed between the forward compressor casing 22 and the midcompressor casing 17. Removable cover 43 is an arcuate member (has arcuate shape).
  • Casing assembly 31 also includes a zero stage seal assembly 39 that is secured to midcompressor casing 17 by removable cover 43.
  • Zero stage seal assembly 39 includes a removable seal support 45 and a seal 47.
  • Removable cover 43 may be fastened to midcompressor casing 17 by means of cover fasteners 49.
  • the removable seal support and seal are joined by means of seal fasteners 51.
  • Figure 3 is a detailed cross section of zero stage seal assembly 39.
  • Zero stage seal assembly 39 includes a t-shaped member 63 having a base 65, a top surface 66, a first projection 67, a side surface 68 and a second projection 69.
  • Seal 47 may include an abradable seal surface, a honeycomb seal surface, a brush seal surface, and/or any seal surface that enables the zero stage seal assembly 39 to function as described herein.
  • Seal surface 70 may be thermally sprayed, brushed, and/or baked, and may be fabricated from a metallic material, a ceramic material, or any other material that enables seal surface 70 to function as described herein.
  • Seal surface 70 may include a plurality of bristles formed from a metallic or non-metallic material, such as ceramics, carbon fiber, and/or silica.
  • Figure 4 is a cross section of a portion of the midcompressor casing 17.
  • the midcompressor casing 17 has a face surface 71, a horizontal inner surface 73 and a vertical inner surface 75.
  • Midcompressor casing 17 has a notch 77 configured to engage the first projection 67 of the zero stage seal assembly 39.
  • the midcompressor casing 17 is additionally provided with a cover groove 79 configured to engage the removable cover 43.
  • Figure 5 is a cross-section of the removable cover 43.
  • Removable cover 43 is provided with a cover notch 81 configured to engage second projection 69 of the zero stage seal assembly 39.
  • forward compressor casing 22 When installed, forward compressor casing 22 is fastened to midcompressor casing 17 and the zero stage seal assembly 39 is disposed in the cavity 82 formed by horizontal inner surface 73, vertical inner surface 75 and notch 77.
  • the zero stage seal assembly 39 is positioned so that first projection 67 of the zero stage seal assembly 39 is disposed in the notch 77 in the midcompressor casing 17. This configuration prevents movement of the zero stage seal assembly 39 in a radial direction.
  • the zero stage seal assembly 39 is secured in place with the removable cover 43.
  • Cover notch 81 is configured to engage second projection 69 of the zero stage seal assembly 39.
  • Forward compressor casing 22 and midcompressor casing 17 maintain the removable cover 43 in place during operation.
  • Fig. 6 is an axial view along longitudinal axis 12 of the first of the plurality of stages 21 looking aft with the forward compressor casing 22 removed.
  • the midcompressor casing 17 may include a casing upper half 87 and a casing lower half 89.
  • the removable seal support 45 may include a plurality of arcuate seal segments 90 such as first upper seal segment 91, first lower seal segment 93, second lower seal segment 95, and second upper seal segment 97 that are removably coupled to an inner surface of midcompressor casing 17.
  • Each of the plurality of arcuate seal segments 90 include a sealing surface extending a full circumferential length along each of the plurality of arcuate seal segments 90.
  • the sealing surface extends a distance above and below a radially inner surface of the midcompressor casing 17 when each of the plurality of arcuate seal segments 90 is coupled the midcompressor casing 17.
  • the seal assembly 25 includes four seal segment, but may include any number of seal segments that enables seal assembly 25 to function as described herein.
  • the removable cover 43 is fastened to the midcompressor casing 17 with cover fasteners 49.
  • the removable cover 43 has a longer peripheral length than any one of the arcuate seal segments 90 (e.g. first upper seal segment 91) so that the individual seal segments can be inserted into the midcompressor casing 17
  • the fasteners may be countersunk into the removable cover 43 and positively captured by the rear face of the forward compressor casing 22.
  • a removable seal support 45 Upon removal of the removable cover 43 access is provided to the end of a removable seal support 45 within either casing upper half 87 or within casing lower half 89.
  • the removable seal support 45 is removably and slidably coupled to midcompressor casing 17. Access to the removable sealing element is provided without having to remove the midcompressor casing 17. Forward face of midcompressor casing 17 may be turned to permit the installation & removal of removable seal support 45 once access is gained when the forward compressor casing 22 is removed.
  • the removable cover 43 is screwed into the midcompressor casing 17 and is positively captured by the rear face of the forward compressor casing 22 during normal operation, eliminating any risk of loose parts causing foreign object damage to the compressor 13.
  • the casing assembly 31 enables the replacement of a zero stage seal assembly 39 without removal of the midcompressor casing 17.
  • the operator can move the zero stage seal assembly 39 by first removing the forward compressor casing 22. This provides access to the removable cover 43 which can then be removed to provide access to the various components of the zero stage seal assembly 39 which can then be easily removed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13197076.6A 2012-12-20 2013-12-13 Ensemble de carter de compresseur donnant accès à un ensemble d'étanchéité d'aubes de compresseur Withdrawn EP2746540A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/721,803 US20140286766A1 (en) 2012-09-11 2012-12-20 Compressor Casing Assembly Providing Access To Compressor Blade Sealing Assembly

Publications (2)

Publication Number Publication Date
EP2746540A2 true EP2746540A2 (fr) 2014-06-25
EP2746540A3 EP2746540A3 (fr) 2017-08-09

Family

ID=49766953

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13197076.6A Withdrawn EP2746540A3 (fr) 2012-12-20 2013-12-13 Ensemble de carter de compresseur donnant accès à un ensemble d'étanchéité d'aubes de compresseur

Country Status (4)

Country Link
US (1) US20140286766A1 (fr)
EP (1) EP2746540A3 (fr)
JP (1) JP2014122624A (fr)
CN (1) CN203867973U (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3058755B1 (fr) * 2016-11-15 2020-09-25 Safran Aircraft Engines Turbine pour turbomachine
US10914318B2 (en) 2019-01-10 2021-02-09 General Electric Company Engine casing treatment for reducing circumferentially variable distortion

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US957887A (en) * 1908-09-28 1910-05-17 Gen Electric Packing for elastic-fluid-turbine shafts.
DE2165528A1 (de) * 1971-12-30 1973-07-12 Kloeckner Humboldt Deutz Ag Einrichtung zum herstellen eines geringen spaltes zwischen den umlaufenden schaufeln und der wandung einer stroemungsmaschine
US3867060A (en) * 1973-09-27 1975-02-18 Gen Electric Shroud assembly
US5501573A (en) * 1993-01-29 1996-03-26 Steam Specialties, Inc. Segmented seal assembly and method for retrofitting the same to turbines and the like
GB9726710D0 (en) * 1997-12-19 1998-02-18 Rolls Royce Plc Turbine shroud ring
US6315519B1 (en) * 1998-09-28 2001-11-13 General Electric Company Turbine inner shroud and turbine assembly containing such inner shroud
FR2794816B1 (fr) * 1999-06-10 2001-07-06 Snecma Stator de compresseur a haute pression
US6226975B1 (en) * 1999-09-14 2001-05-08 Steven G. Ingistov Turbine power plant having a floating brush seal
US6609888B1 (en) * 2000-04-24 2003-08-26 Watson Cogeneration Company Method and apparatus for reducing contamination in an axial compressor
FR2832180B1 (fr) * 2001-11-14 2005-02-18 Snecma Moteurs Revetement abradable pour parois de turbines a gaz
JP4916560B2 (ja) * 2010-03-26 2012-04-11 川崎重工業株式会社 ガスタービンエンジンの圧縮機
US20110299977A1 (en) * 2010-06-03 2011-12-08 General Electric Company Patch ring segment for a turbomachine compressor

Also Published As

Publication number Publication date
EP2746540A3 (fr) 2017-08-09
JP2014122624A (ja) 2014-07-03
US20140286766A1 (en) 2014-09-25
CN203867973U (zh) 2014-10-08

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