EP0475771A1 - Construction de carter de compresseur - Google Patents

Construction de carter de compresseur Download PDF

Info

Publication number
EP0475771A1
EP0475771A1 EP91308357A EP91308357A EP0475771A1 EP 0475771 A1 EP0475771 A1 EP 0475771A1 EP 91308357 A EP91308357 A EP 91308357A EP 91308357 A EP91308357 A EP 91308357A EP 0475771 A1 EP0475771 A1 EP 0475771A1
Authority
EP
European Patent Office
Prior art keywords
case
outer case
compressor
inner case
engine
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.)
Granted
Application number
EP91308357A
Other languages
German (de)
English (en)
Other versions
EP0475771B1 (fr
Inventor
Jesse Eng
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies 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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP0475771A1 publication Critical patent/EP0475771A1/fr
Application granted granted Critical
Publication of EP0475771B1 publication Critical patent/EP0475771B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F01D25/265—Vertically split casings; Clamping arrangements therefor
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins

Definitions

  • This invention relates to the compressor section of gas turbine engines and more particularly to a full hoop case and the stator support means.
  • the compressor case of a gas turbine engine powering aircraft is subjected to severe pressure and temperature loadings throughout the engine operating envelope and care must be taken to assure that the components remain concentric maintaining relatively close running clearances so as to avoid inadvertent rubs.
  • the engine case is thin relative to the rotor and stator components in the compressor section, it responds more rapidly to temperature changes than do other components. This is particularly true during periods of transient engine performance. Typical of these transients are throttle chops, throttle bursts, and the like. Obviously it is customary to provide sufficient clearances during these transients to assure that the rotating parts do not interfere with the stationary parts.
  • the halves are joined at flanges by a series of bolts and the flanges compared to the remaining portion of the circumference of the case is relatively thick and hence does not respond to thermal and pressure changes as quickly as the thinner portion of the case.
  • the consequence of this type of construction is that the case has a tendency to grow eccentrically or out of round.
  • stator vanes tied to a full hoop case for the highest stages of a multiple stage compressor of a gas turbine engine enhanced the structural integrity sufficiently to meet the engine's requirements. Since the stator components, i.e., stator vanes and outer air seals, are segmented the problem was to assure that the compressor maintained its surge margin notwithstanding the fact that the outer case would undergo large deflection at acceleration and deceleration modes of operation.
  • the aft end of the stator may be supported by a bulkhead or a back bone that is formed from a relatively straight shaped annular support that is attached to the inner segmented case and the outer case.
  • the bulkhead or backbone is attached in such a way that the inner case floats axially and circumferentially while being restrained radially. While this arrangement enhances the control of the clearances between the tips of the blades and outer air seal, it is only a portion of the support necessary for the stator.
  • the prevent invention provides a multistage axial flow compressor in or for a gas turbine engine including a drum rotor supporting compressor blades, a segmented stator defining a segmented inner case and having axially spaced rows of stator vanes, an outer case having an axially split portion and a full hoop portion a portion of said inner case being mounted to said full hoop outer case portion so as to be radially restrained but so as to allow its axial displacement and circumferential expansion.
  • the invention provides a method of assembly of a compressor section of a multistage compressor of a gas turbine engine that includes a drum rotor supporting the compressor blades and a plurality of axially spaced segmented stators defining an inner case, a plurality of which are supported by an axially split outer case, comprising the steps of assembling the drum rotor and the stator, mounting an elongate tubular support fixture to a flange of said engine to which a full hoop outer case will be eventually mounted, mounting the full hoop outer case to a sliding support mounted on said tubular support fixture, attaching to the full hoop outer case a supporting mechanism that will support the segmented stator to said full hoop outer case, aligning said supporting mechanism to fit into a complementary formation formed in a supporting structure formed on said inner case, attaching said full hoop outer case to said flange and removing said elongated tubular support fixture , and attaching said axially split outer case to said full hoop
  • a "tongue and groove” arrangement that provides the radial restraint and allows each segment to grow thermally in the axial and circumferential direction.
  • stator vanes are segmented and include a portion of the three rows of vanes in a single casting. When assembled, the segments are mounted end-to-end to form an inner ring-like case and three circumferential rows of spaced vanes.
  • At least this invention provides an improved structural support for a portion of the stators of the high pressure compressor of a gas turbine engine.
  • a feature of this invention is to provide for a compressor drum rotor means for suspending and supporting the stator to the full hoop compressor case that permits axial displacement and circumferential thermal growth of the stator segment while providing radial support and positioning.
  • Fig. 1 is a partial view partly in section and partly in elevation of a multi-stage axial flow compressor for a gas turbine engine.
  • Fig. 2 is a partial sectional view partly in schematic taken along lines 2-2 of Fig. 1 showing one of several segments of the components making up the inner case.
  • Fig. 3 is an exploded view in perspective showing the details of the spool/bolt.
  • Fig. 4 is a perspective view showing the details of a segment of the stator vane.
  • Fig. 5 is a partial view partly in section and partly in elevation showing the method of assembly of a portion of compressor section.
  • Fig. 5A is a view identical to Fig. 5 showing the assembly in another sequence.
  • Fig. 5B is another view identical to Fig 5 and 5A showing the attachment of the outer case to the stator vanes in the final sequence.
  • Fig. 6 is a partial end view in elevation taken along lines 6-6 of Fig. 5B.
  • Fig. 7 is a partial view in section taken along lines 7-7 of Fig. 5B.
  • Figs. 2, 3 and 4 showing part of a multi-stage compressor for a gas turbine engine of the type for powering aircraft.
  • a gas turbine engine reference is made to published descriptions of the F100 family of engines manufactured by Pratt & Whitney, a division of United Technologies Corporation. Suffice it to say that in the preferred embodiment the engine on which this invention is being utilized is a fan-jet axial flow compressor multi-spool type.
  • the compressor section generally indicated by reference numeral 10 is comprised of a plurality of compressor rotors 12 retained in drum rotor 14, where each rotor includes a disk 16 supporting a plurality of circumferentially spaced compressor blades 18.
  • the rotors 12 are suitably supported in an outer engine case 20 and an inner case 22.
  • a portion of the outer case 20 is fabricated in two axial circumferential halves and the other portion is fabricated in a full hoop generally cylindrically shaped case.
  • Fig. 1 the first four lower pressure stages as viewed from the left hand side are housed in the split case and the last three stages are housed in the full case.
  • the problem associated with this construction is that the cavity 44 between the inner case 22 and outer case 34 is ultimately pressurized by the fluid leaking therein from the engine flow path.
  • the engine flow path is defined by the annular passageway bounded by the inner surface of the inner case 22 and outer surface of drum rotor 14.
  • This pressure can reach levels of 5-600 pounds per square inch (PSI) (3446-4136 kNM ⁇ 2). Should a surge situation occur the pressure level in the gas path can reduce instantaneously to a value much lower than the 5-600 PSI (3446-4136 kNM ⁇ 2) and since the pressure in cavity 44 is trapped and can only be reduced gradually, an enormous pressure differential exists across inner case 22.
  • PSI pounds per square inch
  • Spool/bolt 50 ties the inner case 22 to outer case 34 in such a manner as to enhance fatigue life and provide sufficient strength to withstand the compressor surge problems.
  • Spool/bolt 50 comprises a spool member 52 having a reduced diameter threaded portion 54 at its lower extremity adapted to be threaded onto the complementary internal threads 56 formed in boss 58 extending radially from the outer surface 60 of inner case 22.
  • the bolt 62 comprises a relatively long shank 64 carrying threads 65 at the lower extremity and a significantly large head 66.
  • Head 66 may be hexagonally shaped and is thicker and has a longer diameter than otherwise would be designed for this particular sized shank. These unusual dimensions of the head serve to reduce the stress concentration and increase fatigue life of the head to shank fillet adjacent the head.
  • the bolt 62 fits into bore 70 centrally formed in spool 52 that terminates just short of the remote end of the entrance to the bore.
  • the inner diameter of bore 70 is threaded to accommodate the threaded portion of bolt 62.
  • the spool 52 carries a tool receiving portion 72 for threadably securing the spool to inner case 22.
  • the spool 52 is threaded to inner case 22 and the bolt 62 passing through opening 74 in the outer case 34 is threaded to the inner threads of the spool 72, until the head bears against the outer surface of outer case 34 or a suitable washer.
  • Tab washer 76 may be employed to prevent the bolt from inadvertently retracting.
  • the spool serves as a compressed flange-like member thus reducing both bolt fatigue and surge stresses.
  • This configuration resists fatigue loads occasioned by thermal axial deflection differences between outer case 34 and the segmented inner case 22.
  • thread sizes of threads 65 of bolt 62 and threads 54 of spool 52 are different (the threads 54 are specifically designed to be larger). Because the diameter of the spool threads 54 are larger it has a higher disassembly breakaway torque than bolt 62. Consequently, the bolt will, by design, loosen first.
  • the bulkhead 38 or backbone is a load carry member and is generally annularly shaped forming a relatively straight piece but having a radially extending lower portion 40, an angularly extending middle portion 92 and another radially extending upper portion 42.
  • the extremities, i.e. the lower and upper portions 40 and 42 serve basically as flanges and are adapted to be bolted to the inner and upper cases 22 and 20, respectively.
  • the forward face of the lower portion 40 is recessed 10 to accept the radially extending flange 94 integrally formed on the rear end of the inner segmented case 22, forming a somewhat tongue-in-groove arrangement.
  • the inner diameter 96 of bulkhead 38 is dimensioned so that it snugly fits onto the upper surface of the next adjacent stator vane assembly 98 which serves to reduce scrubbing of the case tied assembly, just described.
  • stator vane 30 are cast into unitary segments that when mounted end-to-end in the circumferential direction forms three (3) rows of vanes.
  • the stator vane comprises circumferentially spaced airfoil sections 100 and an inner shroud 102 and an outer shroud 104, the outer shroud defining the inner case.
  • the three rows of vanes are unitary with the outer shroud 104 and each segment abuts the adjacent segment.
  • Groove 106 is provided to receive a suitable seal that serves to minimize leakage between adjacent segments.
  • a plurality of circumferentially spaced removable support segments 120 are bolted by bolts 122 to fit into the recess or groove 124 formed on the inner diameter of the full hoop case 34.
  • a complementary number of hooks 126 are likewise spaced circumferentially around the stator vane segments and extend radially to form a radial "tongue and groove” fit.
  • the "tongue and groove” or dog-bone serve to tie the stator vane or inner case to the outer case and restrain the radial movement of the case.
  • a plurality of lugs 127 are carried at the end of a portion of the segments 120 and sandwich the hook. This can best be seen by referring to Fig. 6 which is a sectional view taken along lines 6-6 of Fig. 5B.
  • the support segment 120 is made removable so that the full hoop case 34 can be assembled or disassembled by sliding over the drum rotor/stator vane assembly.
  • the method of assembly and disassembly is depicted by Figs. 5, 5A and 5B.
  • the full hoop case 34 is retained by one or more mounting fixture 140 (one being shown) which is fixed on one end to the engine's flange 42.
  • the fore flange 144 is affixed to the complementary flange extending from the sliding tube 146.
  • the support 120 is bolted to the case 34 as shown in Fig. 5A.
  • the case 34 is then moved axially to align the aft flanges and the spool/nut 62 (see Fig. 5B), the case 34 then being attached to the flange 42, whereupon the fixture 140 is removed and the bolts are tightened to the requisite torque level.
  • the axially split portion of the outer case may then be attached to the full hoop case 34.The removal of the case, obviously, undergoes the reverse procedures.
  • stator is suspended and supported to the full hoop outer case and the stator is supported in such a way that permits axial movement and circumferential thermal growth while radially constraining the stator.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP91308357A 1990-09-12 1991-09-12 Construction de carter de compresseur Expired - Lifetime EP0475771B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US58121990A 1990-09-12 1990-09-12
US581219 1990-09-12

Publications (2)

Publication Number Publication Date
EP0475771A1 true EP0475771A1 (fr) 1992-03-18
EP0475771B1 EP0475771B1 (fr) 1995-05-10

Family

ID=24324335

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91308357A Expired - Lifetime EP0475771B1 (fr) 1990-09-12 1991-09-12 Construction de carter de compresseur

Country Status (4)

Country Link
EP (1) EP0475771B1 (fr)
KR (1) KR100204743B1 (fr)
DE (1) DE69109590T2 (fr)
TR (1) TR27460A (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2260786A (en) * 1991-10-23 1993-04-28 Snecma Axial flow compressor and maintenance method therefor
GB2261708A (en) * 1991-11-20 1993-05-26 Snecma Turbo-shaft engine casing and blade mounting
EP0566478A1 (fr) * 1992-04-17 1993-10-20 Gec Alsthom Electromecanique Sa Carter haute pression pour turbine à vapeur
EP0962659A3 (fr) * 1998-05-30 2001-03-14 Rolls-Royce Deutschland GmbH Construction du boítier d' une turbine à gaz
FR2846997A1 (fr) * 2002-11-07 2004-05-14 Snecma Moteurs Agencement de montage de secteurs de redresseur
EP1544415A2 (fr) 2003-12-19 2005-06-22 United Technologies Corporation Montage d'aubage fixe pour moteur de turbine à gaz
WO2006059969A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Carter de compresseur à rotation inverse et procédé d'assemblage pour un moteur à turbine en bout
US8267646B2 (en) 2008-08-06 2012-09-18 Rolls-Royce Plc Method of assembling a multi-stage turbine or compressor
WO2014066566A1 (fr) * 2012-10-24 2014-05-01 United Technologies Corporation Formation de drain de rotor de moteur à turbine à gaz
WO2014189564A3 (fr) * 2013-03-06 2015-02-19 United Technologies Corporation Rotor comportant une prétranchée pour turbine à gaz
ITUB20152025A1 (it) * 2015-07-09 2017-01-09 Nuovo Pignone Tecnologie Srl Apparato per la movimentazione di una parte di turbomacchina.
CN113997240A (zh) * 2021-11-02 2022-02-01 中国航发沈阳发动机研究所 一种深轴腔转子装配方法

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002259207A (ja) * 2001-03-02 2002-09-13 Fujitsu Ltd 情報処理装置及び信号処理装置並びにインタフェース装置
WO2006060000A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Ensemble aubes de guidage d'admission de soufflante variable, turbomachine dotee d'un tel ensemble et procede de commande correspondant
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
EP1825113B1 (fr) 2004-12-01 2012-10-24 United Technologies Corporation Boîte de vitesses contre-rotative pour moteur à turbine en bout
WO2006059970A2 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Moteur a turbine equipe d'un ventilateur et d'un compresseur entraines par un engrenage differentiel
EP1825116A2 (fr) 2004-12-01 2007-08-29 United Technologies Corporation Refroidissement par ejecteur de l'enveloppe exterieure d'un moteur a turbine de bout
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
EP1828591B1 (fr) 2004-12-01 2010-07-21 United Technologies Corporation Foyer peripherique pour moteur a turbine de bout
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
EP1828683B1 (fr) 2004-12-01 2013-04-10 United Technologies Corporation Dispositif de combustion pour moteur de turbine
EP2333287A1 (fr) 2004-12-01 2011-06-15 United Technologies Corporation Vectorisation de conduite de transition pour moteur de turbine
US8047778B2 (en) * 2009-01-06 2011-11-01 General Electric Company Method and apparatus for insuring proper installation of stators in a compressor case

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2422026A1 (fr) * 1978-04-04 1979-11-02 Rolls Royce Carter du turbomoteur
EP0073689A1 (fr) * 1981-08-31 1983-03-09 Elliott Turbomachinery Company, Inc. Méthode et dispositif pour contrôler les dilatations thermiques
EP0110757A1 (fr) * 1982-11-08 1984-06-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif de suspension d'aubes statoriques de compresseur axial pour le contrôle actif des jeux entre rotor et stator
FR2591674A1 (fr) * 1985-12-18 1987-06-19 Snecma Dispositif de reglage des jeux radiaux entre rotor et stator d'un compresseur
EP0331837A1 (fr) * 1988-01-11 1989-09-13 General Electric Company Méthode et dispositif de montage d'aubes directrices des turbines

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2422026A1 (fr) * 1978-04-04 1979-11-02 Rolls Royce Carter du turbomoteur
EP0073689A1 (fr) * 1981-08-31 1983-03-09 Elliott Turbomachinery Company, Inc. Méthode et dispositif pour contrôler les dilatations thermiques
EP0110757A1 (fr) * 1982-11-08 1984-06-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif de suspension d'aubes statoriques de compresseur axial pour le contrôle actif des jeux entre rotor et stator
FR2591674A1 (fr) * 1985-12-18 1987-06-19 Snecma Dispositif de reglage des jeux radiaux entre rotor et stator d'un compresseur
EP0331837A1 (fr) * 1988-01-11 1989-09-13 General Electric Company Méthode et dispositif de montage d'aubes directrices des turbines

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2260786A (en) * 1991-10-23 1993-04-28 Snecma Axial flow compressor and maintenance method therefor
GB2260786B (en) * 1991-10-23 1994-09-21 Snecma Maintenance-friendly axial compressor and method of carrying out maintenance
GB2261708A (en) * 1991-11-20 1993-05-26 Snecma Turbo-shaft engine casing and blade mounting
GB2261708B (en) * 1991-11-20 1995-01-25 Snecma Turbo-shaft engine stator
EP0566478A1 (fr) * 1992-04-17 1993-10-20 Gec Alsthom Electromecanique Sa Carter haute pression pour turbine à vapeur
FR2690202A1 (fr) * 1992-04-17 1993-10-22 Alsthom Gec Perfectionnements aux modules haute pression de turbine à rotor tambour avec admission de vapeur à très hautes caractéristiques.
US5350276A (en) * 1992-04-17 1994-09-27 Gec Alsthom Electromecanique Sa High pressure modules of drum rotor turbines with admission of steam having very high characteristics
EP0962659A3 (fr) * 1998-05-30 2001-03-14 Rolls-Royce Deutschland GmbH Construction du boítier d' une turbine à gaz
FR2846997A1 (fr) * 2002-11-07 2004-05-14 Snecma Moteurs Agencement de montage de secteurs de redresseur
EP1544415A2 (fr) 2003-12-19 2005-06-22 United Technologies Corporation Montage d'aubage fixe pour moteur de turbine à gaz
EP1544415A3 (fr) * 2003-12-19 2008-11-12 United Technologies Corporation Montage d'aubage fixe pour moteur de turbine à gaz
WO2006059969A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Carter de compresseur à rotation inverse et procédé d'assemblage pour un moteur à turbine en bout
US8267646B2 (en) 2008-08-06 2012-09-18 Rolls-Royce Plc Method of assembling a multi-stage turbine or compressor
EP2151546A3 (fr) * 2008-08-06 2017-07-19 Rolls-Royce plc Procédé d'assemblage de turbines ou de compresseurs à plusieurs étages
WO2014066566A1 (fr) * 2012-10-24 2014-05-01 United Technologies Corporation Formation de drain de rotor de moteur à turbine à gaz
US9677421B2 (en) 2012-10-24 2017-06-13 United Technologies Corporation Gas turbine engine rotor drain feature
WO2014189564A3 (fr) * 2013-03-06 2015-02-19 United Technologies Corporation Rotor comportant une prétranchée pour turbine à gaz
US10550699B2 (en) 2013-03-06 2020-02-04 United Technologies Corporation Pretrenched rotor for gas turbine engine
ITUB20152025A1 (it) * 2015-07-09 2017-01-09 Nuovo Pignone Tecnologie Srl Apparato per la movimentazione di una parte di turbomacchina.
WO2017005901A1 (fr) * 2015-07-09 2017-01-12 Nuovo Pignone Tecnologie Srl Appareil pour manipuler une partie de turbomachine
CN108026786A (zh) * 2015-07-09 2018-05-11 诺沃皮尼奥内技术股份有限公司 用于搬运涡轮机部件的设备
US10801370B2 (en) 2015-07-09 2020-10-13 Nuovo Pignone Srl Apparatus for handling a turbomachine part
CN113997240A (zh) * 2021-11-02 2022-02-01 中国航发沈阳发动机研究所 一种深轴腔转子装配方法
CN113997240B (zh) * 2021-11-02 2023-03-14 中国航发沈阳发动机研究所 一种深轴腔转子装配方法

Also Published As

Publication number Publication date
DE69109590T2 (de) 1996-02-08
KR100204743B1 (ko) 1999-06-15
KR920006615A (ko) 1992-04-27
DE69109590D1 (de) 1995-06-14
TR27460A (tr) 1995-05-29
EP0475771B1 (fr) 1995-05-10

Similar Documents

Publication Publication Date Title
EP0475771B1 (fr) Construction de carter de compresseur
US5127797A (en) Compressor case attachment means
US5158430A (en) Segmented stator vane seal
US5224824A (en) Compressor case construction
US5127794A (en) Compressor case with controlled thermal environment
US5180281A (en) Case tying means for gas turbine engine
US5302086A (en) Apparatus for retaining rotor blades
EP1247944B1 (fr) Cadre de turbine à gaz
US5118253A (en) Compressor case construction with backbone
US7258525B2 (en) Guide blade fixture in a flow channel of an aircraft gas turbine
EP0202188B1 (fr) Assemblage de rotor de turbine à deux étages
EP2369139B1 (fr) Segment de buse doté d'une bride de poids réduit
US4907944A (en) Turbomachinery blade mounting arrangement
US5176496A (en) Mounting arrangements for turbine nozzles
EP2952689B1 (fr) Espaceur de joint de bordure segmentée pour un moteur à turbine à gaz
US5653581A (en) Case-tied joint for compressor stators
EP0462735A2 (fr) Améliorations concernant les viroles pour des rotors de turbines
US5354174A (en) Backbone support structure for compressor
US5131811A (en) Fastener mounting for multi-stage compressor
EP3508700B1 (fr) Boas ayant des protubérances étendues radialement
US5601404A (en) Integral disc seal
US11230937B2 (en) Turbine shroud assembly with dovetail retention system
US5108261A (en) Compressor disk assembly
EP3246517B1 (fr) Ouvertures de fixation pour distribution de contrainte
EP3269961B1 (fr) Fixation de cône de nez pour moteur à double flux

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17P Request for examination filed

Effective date: 19920908

17Q First examination report despatched

Effective date: 19931004

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REF Corresponds to:

Ref document number: 69109590

Country of ref document: DE

Date of ref document: 19950614

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20070809

Year of fee payment: 17

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20070928

Year of fee payment: 17

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20070904

Year of fee payment: 17

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20080912

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20090529

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080912