WO1987001761A1 - Dispositif annulaire d'etancheite pour un agencement de rotor a aubes - Google Patents

Dispositif annulaire d'etancheite pour un agencement de rotor a aubes Download PDF

Info

Publication number
WO1987001761A1
WO1987001761A1 PCT/US1985/002402 US8502402W WO8701761A1 WO 1987001761 A1 WO1987001761 A1 WO 1987001761A1 US 8502402 W US8502402 W US 8502402W WO 8701761 A1 WO8701761 A1 WO 8701761A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
spacer
ring segment
slot
blades
Prior art date
Application number
PCT/US1985/002402
Other languages
English (en)
Inventor
Philip J. Cederwall
Charles T. Darragh
Warren W. Davis
Boris Glezer
Philip J. Hengen
Original Assignee
Solar Turbines Incorporated
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 Solar Turbines Incorporated filed Critical Solar Turbines Incorporated
Priority to DE8686901729T priority Critical patent/DE3568465D1/de
Priority to JP86502153A priority patent/JPS63500879A/ja
Priority to CA000517815A priority patent/CA1235071A/fr
Publication of WO1987001761A1 publication Critical patent/WO1987001761A1/fr

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • This invention relates generally to gas turbine engine rotors and more particularly to the device for retaining the blades of a bladed rotor against axial movement on the rotor, sealing the gaps
  • Turbine rotor assemblies having removable ⁇ _5 blades have been used in gas turbine engines and turbochargers to reduce cost and increase serviceability over one-piece rotors.
  • the ability to replace worn or damaged blades rather than replacing the entire rotor has allowed the engineer to strive for
  • the current rotor assemblies consist of a forged rotor hub which is machined to accept a plurality of individual blades. The root portion of the blades are assemblied on the hub to prevent
  • a seal ring is attached to the hub to prevent the blades from moving axially out of the hub and to prevent the passage of working gases between the hub and the root portion of the blade.
  • the seal causes all the working gas to pass through the working portion of the blade and increases the operating efficiency of the engine.
  • I ' CC a half-round groove which cooperates with the half-round groove in the segments.
  • the blades are assembled in the rotor; the segments are inserted in the groove of the blade and a lock wire is circumferentially inserted into the two half-round
  • a rotor assembly which consists of a plurality of attaching slots and lugs on the disk, a plurality of blades equal in number to the slots and a one-piece sideplate has lugs thereon.
  • the sideplate is positioned on the rotor with the blades
  • the seal ring is positioned between the seal plate segments and the blade at one end, and between the seal plate segments and the turbine wheel at the other end. After installation of the seal ring each of the seal plate segments are conventionally installed.
  • the disadvantages of the above noted rotor assembly constructions are that they increase the manufacturing cost, are difficult to service, and reduce the dependability of the rotor assembly.
  • the Guy et al patent increases manufacturing and assembly costs by requiring two half-round grooves and two lock wires which must be fed into the two half-round grooves and bent radially inwardly to prevent the wire from passing too far into the groove.
  • the Trenschel et al patent increases manufacturing and assembly cost by using a plurality of lugs on both the rotor and the sideplate. The lugs require machined tapers to mate with each other and the assembly technique requires special tooling such as heating facilities and a press.
  • the Thompson patent increases manufacturing and assembly costs due to the addition of a complex shaped seal ring and a complex machining configuration of the turbine wheel retainer area.
  • the above patents describe expensive bladed rotor assembly employing complex machining and assembly techniques.
  • the seal ring must be removed from the rotor to replace a single failed blade and then requires that the complex assembly technique be followed to reassembly.
  • the present invention is directed to overcoming one or more of the problems as set forth above.
  • a bladed rotor assembly comprises a rotor having opposed faces, a rim and a plurality of circumferentially arrayed retention slots in the rim.
  • the slots pass from one of the faces to the other of the faces and have a radial retention means.
  • a plurality of blades are mounted on the rotor and each of the blades have a root portion received in a corresponding one of the slots. The root portion is shaped so that it engages the radial " retention means to prevent movement of the blade radially outward of the rotor.
  • a means is provided on the rotor and on- each of the plurality of blades defining an annular T-slot at one of the faces and.
  • a seal means is rotatably trapped in the T-slot and includes a ring segment means having first and second ends circumferentially spaced apart to define a space therebetween and a spacer is positioned between the ends of the ring segment means.
  • the seal means is indexed to a position at which the spacer is out of alignment with the opening in the rotor and a means for preventing relative rotation between the seal means and the rotor is included.
  • a gas turbine comprises a bladed rotor assembly including a rotor having opposed faces, a rim and a plurality of circumferentially arrayed retention slots in the rim.
  • the slots pass from one of the faces to the other of the faces and has a radial retention means.
  • a plurality of blades are mounted on the rotor with each of the blades having a root portion received in a corresponding one of the slots.
  • the root portion is shaped so that it engages the radial retention means to prevent movement of the blade radially outward of the rotor.
  • a means on the rotor and on each of the plurality of blades defines an annular T-slot at one of the faces and a means defines an opening in said means on the rotor which forms a portion of the T-slot.
  • a seal means is rotatably trapped in the T-slot and includes a ring segment means having first and second ends circumferentially spaced apart to define a space
  • the seal means is indexed to a position at which the spacer is out of alignment with the opening in the rotor and a means for preventing relative rotation between the seal means and
  • the rotor assembly includes a rotor having opposed faces, a rim and a plurality of
  • the slots pass from one of the faces to the other of the faces and has a radial retention means.
  • a plurality of blades are mounted on the rotor with each of the blades having a root portion received in a
  • a means on said rotor forming a circumferentially extending radially outwardly facing
  • 30 comprises the steps of: positioning ring segment means in the groove formed in the rotor so that a space defined between circumferentially spaced apart first and second ends is aligned with one of the slots in the rotor; inserting the root portion of a blade through
  • the present invention provides a simple and inexpensive method of replacing individual worn or damaged blades of a rotor assembly.
  • the means for preventing rotation are removed and the seal means which is rotatably trapped in the T-slot is indexed so that the ends of the ring segment means align with the opening in the rotor and the spacer is removed.
  • the ring segment means is rotated until the ends align with the worn or damaged blades to be removed and replaced.
  • the seal means is indexed to a position at which the spacer is out of alignment with the opening in the rotor, and the means for preventing rotation is secured to the rotor.
  • the present invention provides for a simple and inexpensive means to attach a plurality of blades to a rotor while providing a seal to insure the flow of working gases through the working portion of the turbine blades and for dampening blade vibration.
  • the assembly technique is simple and easy to employ. The use of heavy presses for assembly or disassembly and complex machining configuration have been eliminated.
  • the present invention is simple to employ, allows for the flexibility of replacing a single or a plurality of worn or damaged blades and does not require a complexity of machining or assembly fixtures.
  • Figure 1 is a view of a gas turbine engine employing the present invention
  • Figure 2 is an end view of a rotor assembly embodying the present invention
  • Figure 3 is a sectional view along lines
  • Figure 4 is an end view of a rotor assembly including an alternate embodiment of the present invention.
  • a bladed rotor assembly 10 is shown in a gas turbine engine 12.
  • the rotor assembly 10 is comprised of a rotor 14, a plurality of blades 16, means 18 on the rotor and on each of the plurality of blades for defining an annular T-slot 20, means 22 defining an opening 23 in the rotor 14 to provide access to a portion of the T-slot 20, means 24 for sealing positioned in the T-slot 20 and means 26 for preventing relative rotation between the means 24 for sealing and the rotor 14.
  • the rotor 14 as shown in Figures 2 and 3, has a center hub 28 and a rim 30 at its perimeter.
  • the rotor 14 has opposite first and second faces 34,36, of which the first face 34 is stepped or multilevel, a plurality of blind holes 38 in the first face 34 and a plurality of circumferentially arrayed retention slots 40 positioned in the rim 30.
  • the slots 40 extend from one face 34 to the other face 36 and have a radial retention means 42 which includes a pair of side walls 43 which are undercut in a conventional manner to provide at least one inwardly directed abutment face 44 on each side wall.
  • the plurality of blades 16 are mounted on the rotor 14.
  • Each of the plurality of blades has a root section 46 which engages a corresponding slot 40 and is spaced away from a bottom 50 of the slot 40 in the rotor 14.
  • the root portion 46 is shaped so that it engages the abutment face 44 of the rotor 14.
  • Each blade 16 has a platform section 52 disposed radially outwardly from the periphery of the rim 30 by an extended neck region 54 of the blade 16.
  • Each blade has a lip 56 projecting radially inward from the root section 46 and abuts a portion of the multilevel surface of the first face 34.
  • the means 18 on the rotor 14 for defining a portion of the T-slot 20 includes a circumferentially extending radially outwardly facing groove 62 which extends axially outward from the first face 34 of the rotor 14.
  • the means 18 on each blade 16 for defining a portion of the T-slot 20 includes a circumferentially extending radially inwardly facing groove 64 formed on each blade 16 intermediate the root section 46 and the platform section 52 and on the same side as the lip 56.
  • the opening 23 in said means 18 on the rotor 14 which forms a portion of the T-slot 20 opens into the groove 62 and has an arcuate length D_ for purposes to be defined later.
  • the means 24 for sealing includes a ring segment means 74 having first and second ends 76,78 circumferentially spaced apart to define a space 80 therebetween, and a segment shaped spacer 82 positioned in the space 80.
  • the spacer 82 has a circumferential length slightly less than the circumferential length of the space to define a controlled gap 84 or clearance between the spacer 82 and on both of the ends 76,78 for a later defined purpose.
  • the arcuate length D_ of the opening 23 is at least equal to the length of the spacer 82.
  • the ring segment means 74 of the embodiment of Fig. 2 is a single ring segment 86 with the ends 76,78 being the ends thereof.
  • the ring segment means 74 and the spacer 82 each have an inner edge 88 and an outer edge 90.
  • the inner edges 88 are received in the outwardly facing groove 62 of the rotor 14 and the outer edges 90 are received in the inwardly facing groove 64 of each blade 16.
  • the inner edge 88 of the ring segment means 74 has an inner leg portion 92 which is angled away from the first face 34 on the rotor 14 and the outer edge 90 has an outer leg portion 94 which angles away from the root portion 46 of the blade 16.
  • the means 26 for preventing relative rotation between the means for sealing 24 and the rotor 14 as shown in Fig.
  • the pin 100 includes a hole 100 extending through one of the spacer 82 and ring segment means (74) , one of the blind holes 38 in the first face of the rotor 14, and a pin 102 having a diameter slightly smaller than the holes 100,38.
  • the pin 102 has a hollow recess in one end.
  • the pin 100 could be a rivet or a bolt inserted through the holes 100 in the spacer 82 and the blind holes would be through drilled in rotor 14.
  • FIG. 4 Another alternative shown in Figure 4 includes a segmented ring 76 made up of three sectors 104.
  • the segments will be made to provide ends 106,108 equivalent to those ends 76,78 of the single ring and are- spaced apart ends of two of the sectors 104.
  • the means 26 for preventing relative rotation between the sealing means 24 and the rotor 14 would still remain a single pin 102; however, a plurality of pins could be used.
  • each of the sectors 104 and the spacer 82 have a hole 100 and a plurality of pins 102 may be used to secure the sealing means 24-to the rotor 14.
  • the bladed rotor assembly 10 is preassembled prior to assembly into a gas turbine engine 12.
  • the single ring segment 86 is assembled into the groove 76 by spreading the ends 76,78 of the single ring segment 86 over the rotor and releasing the ends with the single ring segment 86 positioned in the groove 76.
  • one end of the single ring segment 86 could be inserted through the opening 23 in the rotor 14 and threaded around the groove 62 so that the inner leg portion 88 of the segment 76 is trapped within the groove 62 in the rotor 14.
  • the space 80 between the first and second ends 76,78 of the segment 86 is aligned with one of the slots 40 in the rim 30 of the rotor 14 so that the root portion 46 of the blade 16 will pass therethrough.
  • the plurality of turbine blades 16 is inserted into that slot 40 from the first face 34 side until the lip 56 contacts the first face 34.
  • the groove 64 is radially aligned with the groove 62 to form a short portion of the T-slot 20.
  • the segment 86 is indexed to align the space 80 with another of the slots 40 in the rotor 14. In so doing, a portion of the segment 86 enters the short portion of the T-slot and locks the blade to the rotor in an axial direction.
  • the root portion 46 of a second blade 16 is then inserted into the slot 40 aligned with the space 80 and the segment 86 is again indexed to lock the second blade to the rotor 14 and the space 80 is aligned with the next adjacent slot.
  • the sequence of inserting a blade 16 in the slot 40 and indexing the segment 86 is repeated until all the slots 40 contain a blade 16.
  • the single ring segment 86 is then rotated to align the space 80 with the opening 23 in the rotor 14.
  • the leg portion 94 of the outer edge 90 of the spacer 82 is positioned in the inwardly facing groove 64 formed by the blades 16.
  • the segment 86 and spacer 82 are rotated within the T-slot 20 until the hole 100 in the spacer 82 aligns with one of the blind holes 38 in the rotor 14 at which position the spacer 82 is out of alignment with the opening 23 in the rotor 14 and the gap 84 is positioned so that the space between the rotor 14 and the bottom 50 of the blade 16 do not coincide.
  • the pin 102 is inserted through the hole 100 in the spacer 82 into the blind hole 38 in the rotor 14 with the hollow end toward the rotor and fixedly attached to the rotor 14 using a punch and a hammer.
  • the hollow end is expanded in the hole 38 by tapping the punch against the pin 102 with the hammer.
  • the above described assembly can be varied when using a plurality of sectors 104 to make up the single ring segment 86.
  • a plurality of sectors 104 to make up the single ring segment 86.
  • almost two-thirds of the blades 16 can be inserted into the slots 40 in the rotor 14 before the sectors 104 must be aligned and inserted into the annular T-slot 20.
  • the third sector must be inserted in the outwardly facing groove 62 in the rotor 14.
  • the indexing and aligning process as described earlier is now utilized until the remainder of the blades 16 are inserted into the slots 40.
  • the procedure for inserting the spacer 82 and the pin 102 is the same as above.
  • the bladed rotor assembly 10 will be assembled by a conventional manner into a gas turbine engine 12.
  • heat is absorbed in the thin spacer 82 and the single ring segment 86 at a high rate wherein the mass of the rotor absorbs heat at a slower rate. Therefore, the controlled gap 84 between the single ring segment 86 and the spacer 82 will be filled due to the difference in the rate of heat absorbed in the masses in the start up mode. As the engine continues to warm up and enters the steady state mode, the controlled gap 84 will reoccur.
  • the primary advantage of the bladed rotor assembly 10 of this invention is in the unique construction of the ring segment means 74 and the spacer 82, and the simple assembly technique which can be used to make a new rotor or repair a damaged rotor. For example, when the bladed rotor assembly 10 has failed a blade 16 and requires that the blade be replaced the rotor assembly 10 will be removed from the engine using conventional disassembly techniques.
  • the pin or pins 102 which prevent the means for sealing 24 from rotating relative to the rotor 14 are removed.
  • the ends 76,78 of the single ring segment 86 are aligned with the opening 23 in the rotor 14 and the spacer 82 is removed from the inwardly facing groove 64 formed by the blades 16.
  • the ends 76,78 of the single ring segment 86 are rotated to align with the damaged blade 16, the blade 16 is removed from the slot 40 in the rotor 14 and a new blade 16 is replaced in the slot 40.
  • the single ring segment 86 can be rotated to align with each damaged blade 16 and the blade 16 can be replaced. This process continues until all of the worn or damaged blades 16 are replaced.
  • the spacer 82 is repositioned and the pin or pins 102 are secured as discussed earlier.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Des agencements de rotor à aubes amovibles sont utilisés avec des turbines à gaz pour réduire les coûts et accroître la facilité d'entretien. Des structures complexes ont été utilisées dans le passé pour maintenir les aubes dans le rotor et pour sceller l'espace intermédiaire. Des outils et des procédés complexes étaient nécessaires pour remplacer des aubes usées ou endommagées. Le remplacement des aubes selon cette invention rend l'entretien moins complexe et réduit les coûts de maintenance. L'agencement (10) de rotor à aubes comprend un rotor (14) pourvu de fentes (40), une rainure (62) tournée vers l'extérieur et un évidement (23) dans le rotor (14). Les aubes (16) sont montées dans les fentes (40) et pourvues d'une rainure (64) tournée vers l'intérieur. Les rainures (62, 64) forment une fente annulaire en T (20). Un segment annulaire (74) et une pièce d'écartement (82) sont piégés de façon rotative dans la fente en T (20) et un dispositif (26) empêche la rotation du segment annulaire (74) et/ou de la pièce d'écartement (82) par raport au rotor (14). L'agencement de rotor (10) permet le remplacement individuel d'aubes endommagées (16) par une technique de démontage-montage simple, peu coûteuse et à l'aide d'outils peu coûteux. Le dispositif anti-rotatif (26) est enlevé du rotor et on met en rotation le segment annulaire (74) et la pièce d'écartement (82) jusqu'à aligner l'évidement (23) et la pièce d'écartement (82). On fait glisser la pièce d'écartement (82) pour l'enlever de la fente en T (20). Le segment annulaire (74) est aligné de façon à permettre le remplacement de chaque aube endommagée (16). Une fois que l'on a remplacé toutes les aubes endommagées (16), on aligne le segment annulaire (74) avec l'évidement, on ré-intoduit la pièce d'écartement (82) et on met en rotation le segment annulaire (74) et la pièce d'écartement (82) jusqu'à une position où le dispositif anti-rotatif (26) est attaché de manière fixe au rotor (14).
PCT/US1985/002402 1985-09-12 1985-12-06 Dispositif annulaire d'etancheite pour un agencement de rotor a aubes WO1987001761A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE8686901729T DE3568465D1 (en) 1985-09-12 1985-12-06 Seal ring means for a bladed rotor assembly
JP86502153A JPS63500879A (ja) 1985-09-12 1985-12-06 羽根付きロ−タ−組立体のためのシ−ルリング装置
CA000517815A CA1235071A (fr) 1985-09-12 1986-09-09 Bague d'etancheite pour rotor a aubes

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US77545185A 1985-09-12 1985-09-12
US775,451 1985-09-12

Publications (1)

Publication Number Publication Date
WO1987001761A1 true WO1987001761A1 (fr) 1987-03-26

Family

ID=25104469

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1985/002402 WO1987001761A1 (fr) 1985-09-12 1985-12-06 Dispositif annulaire d'etancheite pour un agencement de rotor a aubes

Country Status (5)

Country Link
EP (1) EP0236337B1 (fr)
JP (1) JPS63500879A (fr)
CA (1) CA1235071A (fr)
DE (1) DE3568465D1 (fr)
WO (1) WO1987001761A1 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2603333A1 (fr) * 1986-09-03 1988-03-04 Snecma Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage
US4980774A (en) * 1988-07-21 1990-12-25 Magnascreen Corporation Modular flat-screen television displays and modules and circuit drives therefor
US4982272A (en) * 1988-07-21 1991-01-01 Magnascreen Corporation Modular flat-screen color television displays and modules and circuit drives therefor
US5068740A (en) * 1988-07-21 1991-11-26 Magnascreen Corporation Modular flat-screen television displays and modules and circuit drives therefor
US5079636A (en) * 1988-07-21 1992-01-07 Magnascreen Corporation Modular flat-screen television displays and modules and circuit drives therefor
EP0761930A1 (fr) * 1995-08-24 1997-03-12 ROLLS-ROYCE plc Segments d'étanchéité et de rétention pour les aubes d'une turbomachine
EP1944471A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'une rotor de turbine
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
FR3127255A1 (fr) * 2021-09-23 2023-03-24 Safran Aircraft Engines Ensemble rotatif pour turbomachine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2939832B1 (fr) * 2008-12-11 2011-01-07 Turbomeca Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque.

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB905582A (en) * 1960-05-26 1962-09-12 Rolls Royce Improvements relating to the sealing of blades in a bladed rotor
GB954323A (en) * 1962-03-17 1964-04-02 Rolls Royce Improvements in or relating to bladed rotors for fluid flow machines such as turbines
US3300179A (en) * 1966-04-22 1967-01-24 Gen Motors Corp Blade stalk cover plate
GB1095830A (en) * 1966-09-13 1967-12-20 Rolls Royce Bladed rotor for a fluid flow machine such as a gas turbine engine
FR1580473A (fr) * 1967-07-13 1969-09-05
FR2524933A1 (fr) * 1982-04-13 1983-10-14 Snecma Dispositif de verrouillage axial d'aubes de rotor de turbine ou de compresseur

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB905582A (en) * 1960-05-26 1962-09-12 Rolls Royce Improvements relating to the sealing of blades in a bladed rotor
GB954323A (en) * 1962-03-17 1964-04-02 Rolls Royce Improvements in or relating to bladed rotors for fluid flow machines such as turbines
US3300179A (en) * 1966-04-22 1967-01-24 Gen Motors Corp Blade stalk cover plate
GB1095830A (en) * 1966-09-13 1967-12-20 Rolls Royce Bladed rotor for a fluid flow machine such as a gas turbine engine
FR1580473A (fr) * 1967-07-13 1969-09-05
FR2524933A1 (fr) * 1982-04-13 1983-10-14 Snecma Dispositif de verrouillage axial d'aubes de rotor de turbine ou de compresseur

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2603333A1 (fr) * 1986-09-03 1988-03-04 Snecma Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage
US4730983A (en) * 1986-09-03 1988-03-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" System for attaching a rotor blade to a rotor disk
EP0263002A1 (fr) * 1986-09-03 1988-04-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Dispositif d'étanchéité et de verrouillage axial d'aubes d'une turbomachine
US4980774A (en) * 1988-07-21 1990-12-25 Magnascreen Corporation Modular flat-screen television displays and modules and circuit drives therefor
US4982272A (en) * 1988-07-21 1991-01-01 Magnascreen Corporation Modular flat-screen color television displays and modules and circuit drives therefor
US5068740A (en) * 1988-07-21 1991-11-26 Magnascreen Corporation Modular flat-screen television displays and modules and circuit drives therefor
US5079636A (en) * 1988-07-21 1992-01-07 Magnascreen Corporation Modular flat-screen television displays and modules and circuit drives therefor
EP0761930A1 (fr) * 1995-08-24 1997-03-12 ROLLS-ROYCE plc Segments d'étanchéité et de rétention pour les aubes d'une turbomachine
EP1944471A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'une rotor de turbine
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
FR3127255A1 (fr) * 2021-09-23 2023-03-24 Safran Aircraft Engines Ensemble rotatif pour turbomachine

Also Published As

Publication number Publication date
DE3568465D1 (en) 1989-04-06
EP0236337B1 (fr) 1989-03-01
JPS63500879A (ja) 1988-03-31
CA1235071A (fr) 1988-04-12
EP0236337A1 (fr) 1987-09-16

Similar Documents

Publication Publication Date Title
US5302086A (en) Apparatus for retaining rotor blades
US5205708A (en) High pressure turbine component interference fit up
US5277548A (en) Non-integral rotor blade platform
US4505640A (en) Seal means for a blade attachment slot of a rotor assembly
US4659285A (en) Turbine cover-seal assembly
KR970001123B1 (ko) 연소 터어빈용 압축기 다이어프램 조립체
RU2315184C2 (ru) Роторный узел турбомашины с двумя снабженными лопатками дисками, разделенными распоркой
US7086830B2 (en) Tube-type vortex reducer with retaining ring
CA2264282C (fr) Separateur d'air de turbine a gaz
US4676715A (en) Turbine rings of gas turbine plant
EP0297120B1 (fr) Joint d'etancheite inter-aubes pour rotor de turbomachine
US4426191A (en) Flow directing assembly for a gas turbine engine
CA1164348A (fr) Organe d'orientation de l'ecoulement pour turbomoteur a gaz
EP0134186B1 (fr) Assemblage de stator pour turbines
CN103917761B (zh) 一种燃气涡轮机装置及其进气壳组件的装配方法
EP1444419B1 (fr) Structure de soutenement d'aubes
US20090096174A1 (en) Blade outer air seal for a gas turbine engine
US4626169A (en) Seal means for a blade attachment slot of a rotor assembly
EP0236337B1 (fr) Dispositif annulaire d'etancheite pour un agencement de rotor a aubes
EP2606204B1 (fr) Logement de garniture d'étanchéité intermédiaire équipé d'une bande d'usure remplaçable
EP0222679B1 (fr) Plaque de couverture pour un disque de turbine
US7497658B2 (en) Stacked reaction steam turbine stator assembly
US7407370B2 (en) Axial and circumferential seal for stacked rotor and/or stator assembly
US6471478B1 (en) Axial seal system for a gas turbine steam-cooled rotor
US5395211A (en) Stator structure for a rotary machine

Legal Events

Date Code Title Description
WWE Wipo information: entry into national phase

Ref document number: 1986901729

Country of ref document: EP

AK Designated states

Kind code of ref document: A1

Designated state(s): JP

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): CH DE FR GB SE

WWP Wipo information: published in national office

Ref document number: 1986901729

Country of ref document: EP

WWG Wipo information: grant in national office

Ref document number: 1986901729

Country of ref document: EP