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US3918842A - Blade assembly for a fluid flow machine - Google Patents

Blade assembly for a fluid flow machine Download PDF

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Publication number
US3918842A
US3918842A US475916A US47591674A US3918842A US 3918842 A US3918842 A US 3918842A US 475916 A US475916 A US 475916A US 47591674 A US47591674 A US 47591674A US 3918842 A US3918842 A US 3918842A
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United States
Prior art keywords
groove
rotor assembly
face
blades
platforms
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.)
Expired - Lifetime
Application number
US475916A
Inventor
Peter John Longley
Anthony George Gale
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Rolls Royce PLC
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Rolls Royce 1971 Ltd
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Publication date
Application filed by Rolls Royce 1971 Ltd filed Critical Rolls Royce 1971 Ltd
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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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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

Definitions

  • ABSTRACT 1 1 Foreign Application Priority Data
  • a bladed rotor for a gas turbine engine the shrouds June 26. 1973 United Kingdom 30252/73 or platforms of the blades each have a face which c0- operates with a corresponding face on the next adja- [52] US. Cl 416/219; 416/193 cent blade to form a radially tapering groove whose [51] Int. Cl. F01D 5/18; FOlD 5/24 width decreases as the radial distance from the rotor [58] Field of Search 416/191, 193, 219, 221 axis increases. and a sealing member such as a wire is mounted in the groove to seal between the adjacent [56] References Cited platforms or shrouds.
  • At least one projection from said face or faces adapted to prevent said sealing member falling radially inward to disengage from the groove.
  • the groove may be formed between a radial surface on one face and an inclined surface on the corresponding face, or between an inclined surface on one face and an oppositely inclined surface on the corresponding face.
  • the sealing member comprises a wire which is curved longitudinally to match the curve of said tapered groove.
  • FIG. 1 shows a diagrammatic view of a gas turbine engine showing an embodiment of the present invention
  • FIG. 2 shows an enlarged pictorial view of the embodiment shown at FIG. 1,
  • FIG. 3 shows a section taken between two respective blades shown at FIG. 2,
  • FIG. 4 shows an end elevation of two adjacent blade roots taken in direction of arrow 4 at FIG. 3,
  • FIG. 5 shows an enlarged pictorial view of the sealing member
  • I FIG. 6 is a view similar to FIG. 2 but of a second embodiment of the invention.
  • a gas turbine engine shown generally at 10 comprises an intake 12, compressor section 13, combustion section 14 and turbine section 15 terminating in exhaust nozzle 16.
  • a brokenaway portion of the casing round the turbine section 15 shows diagrammatically the turbine rotor in accordance with the invention.
  • FIG. 2 is an enlarged pictorial view of the broken away section shown at FIG. 1 and shows individual aerofoil shaped turbine blade members a, 20b, 20c and 20d terminating in blade root portions 21a, 21b, 21c and 21d only three of which are wholly or partially exposed in the drawings, the blade roots in turn are secured in the rotor disc (not shown) by means of fir tree root members.
  • the outer tips of the blades 20a, b, c, d, etc. are in turn bounded by a shroud portion 22 which it will be appreciated may also be provided with a similar sealing system as that shown at the blade roots.
  • the surface 25 is provided with a recessed portion 25', the recess terminating in an inclined arcuate surface 27 against which the arcuate wire sealing member 28 rests.
  • the inclined surface 27 and flat surface 26 together form a tapered groove whose width decreases as the radial distance from the rotor axis increases, and the wire 28 is of the same length as the root portion of the blade.
  • This construction can also be seen at FIG. 4.
  • the sealing members 28 are prevented from moving radially inwardly by means of a projecting portion 29 being provided upon the substantially flat surface 26, the projection 29 being spaced radially inward of that part of the flat surface 26 which corresponds with the inclined surface 27.
  • the sealing members and blades are prevented from moving axially from the disc by means of lock plates 30 and 31 shown in more detail at FIG. 3.
  • FIG. 6 shows a further embodiment of the invention, in this case the sealing member 28 is arranged to nestle in the tapered arcuate groove formed between two inclined arcuate step portions 32 provided upon the radially outermost surfaces of two recessed portions one of which is provided on each side of the blade root portion; again cooperating projections 33 radially inward of the surfaces 32 prevent the member 28 falling radially inwardly.
  • sealing members 28 are interposed between the platforms, they prevent these platforms fretting against one another, and their position at the inner end of the aerofoil enables them to provide damping of this area; clearly the faster the rotor rotates, the more centrifugal load acts on the sealing members and the greater will be the damping. It will also be understood that expansion or contraction occurring in the turbine may be accommodated by the above mentioned sealing arrangements.
  • seal members 28 in arcuate form the curved shape gives angular location to enable the ends of the seal member to be shaped by machining to conform with the surface of the blade front and rear faces 21a and 21b etc.
  • the arcuate shape also prevents twisting of the seal member 28 and ensures friction damping.
  • a bladed rotor assembly for a gas turbine engine comprising a rotor and a plurality of angularly spaced apart aerofoil blades supported from the rotor, each blade having a platform member, said platform member having a face which cooperates with a corresponding face on the next adjacent blade to form a radially tapering groove whose width decreases as its distance from the rotor axis increases, said radially tapering groove being curved longitudinally relative said rotor assembly, and a sealing member mounted in the tapered and longitudinally curved groove so as to seal between the adjacent platforms, said sealing member comprising a wire curved longitudinally relative said rotor assembly and being substantially complementary to the longitudinal curve of said groove.

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

Abstract

In a bladed rotor for a gas turbine engine the shrouds or platforms of the blades each have a face which cooperates with a corresponding face on the next adjacent blade to form a radially tapering groove whose width decreases as the radial distance from the rotor axis increases, and a sealing member such as a wire is mounted in the groove to seal between the adjacent platforms or shrouds.

Description

United States Patent Longley et a1.
1 1 Nov. 11, 1975 BLADE ASSEMBLY FOR A FLUID FLOW 2.912.223 11/1959 111111 416/221 MACHINE 3.112.915 12/1963 Morris 416/220 3.266.770 8/1966 Harlow 416/220 1 Inventors: Peter J g y, Hllton; Anthony 3.709.631 1/1973 Karstensen 416/220 x George Gale. Wollaton, both of 3.752.598 8/1973 Bowers et a1. 416/220 UX England 3.834.831 9/1974 Mitchell 416/193 X [73] Assignee: Rolls-Royce (1971) Limited,
London. England Prmmry E.\anuner-E verette A. Powell, Jr. Attorney, Agent, or F1/'m-Cushman, Darby & [22] Filed: June 3, 1974 C h [21] Appl. No.: 475,916
[57] ABSTRACT 1 1 Foreign Application Priority Data In a bladed rotor for a gas turbine engine the shrouds June 26. 1973 United Kingdom 30252/73 or platforms of the blades each have a face which c0- operates with a corresponding face on the next adja- [52] US. Cl 416/219; 416/193 cent blade to form a radially tapering groove whose [51] Int. Cl. F01D 5/18; FOlD 5/24 width decreases as the radial distance from the rotor [58] Field of Search 416/191, 193, 219, 221 axis increases. and a sealing member such as a wire is mounted in the groove to seal between the adjacent [56] References Cited platforms or shrouds.
UNITED STATES PATENTS 7 Claims, 6 Drawing Figures 2.445.154 7/1948 Reed 416/221 lfl/ Patent N'ov.11,1975 Sheet1of3 3,918,842
US. Patent Nov. 11, 1975 Sheet 2 of3 3,918,842
Nov. 11, 1975 Sheet3of3 3,918,842
US. Patent BLADE ASSEMBLY FOR A FLUID FLOW MACHINE This invention concerns a bladed rotor for a gas turbine engine.
In the bladed rotors of gas turbine engines, it is normally necessary to provide sealing means between the parts of adjacent blades which form part of theflow annulus, i.e., between the root platforms and/or between the shrouds.
In the past there have been many systems available for providing these seals, however, most of them have suffered from a similar defect in that whilst the seals may be extremely efficient while the rotor is stationary, when the rotor is running at a comparatively high rotational speed the centrifugal force acting upon it tends to make it expand and therefore make the seals less effective. Other difficulties are encountered with the sealing of a turbine rotor due to expansion of the turbine components caused by large change in temperature at which the turbine operates.
It has been found that by use of an embodiment of erates with a corresponding face on the next adjacent blade to form a radially tapering groove whose width decreases as the distance from the rotor axis increases in which a sealing member is mounted so as to seal between the adjacent platforms or shrouds.
Preferably there is at least one projection from said face or faces adapted to prevent said sealing member falling radially inward to disengage from the groove.
The groove may be formed between a radial surface on one face and an inclined surface on the corresponding face, or between an inclined surface on one face and an oppositely inclined surface on the corresponding face.
In a preferred embodiment the sealing member comprises a wire which is curved longitudinally to match the curve of said tapered groove.
The invention will now be particularly described merely by way of example with reference to the accompanying drawings in which:
FIG. 1 shows a diagrammatic view of a gas turbine engine showing an embodiment of the present invention,
FIG. 2 shows an enlarged pictorial view of the embodiment shown at FIG. 1,
FIG. 3 shows a section taken between two respective blades shown at FIG. 2,
FIG. 4 shows an end elevation of two adjacent blade roots taken in direction of arrow 4 at FIG. 3,
FIG. 5 shows an enlarged pictorial view of the sealing member, and I FIG. 6 is a view similar to FIG. 2 but of a second embodiment of the invention.
Referring to FIG. 1 a gas turbine engine shown generally at 10 comprises an intake 12, compressor section 13, combustion section 14 and turbine section 15 terminating in exhaust nozzle 16. A brokenaway portion of the casing round the turbine section 15 shows diagrammatically the turbine rotor in accordance with the invention. I
FIG. 2 is an enlarged pictorial view of the broken away section shown at FIG. 1 and shows individual aerofoil shaped turbine blade members a, 20b, 20c and 20d terminating in blade root portions 21a, 21b, 21c and 21d only three of which are wholly or partially exposed in the drawings, the blade roots in turn are secured in the rotor disc (not shown) by means of fir tree root members. The outer tips of the blades 20a, b, c, d, etc. are in turn bounded by a shroud portion 22 which it will be appreciated may also be provided with a similar sealing system as that shown at the blade roots.
Referring to the sealing arrangement shown generally at 24 it will be appreciated that a slight clearance must be allowed at the abutting surfaces 25 and 26 provided on the blade root portions for manufacturing tolerance, and it is therefore necessary to provide a seal to prevent any through flow of air or gas through this gap.
It will be seen that the surface 25 is provided with a recessed portion 25', the recess terminating in an inclined arcuate surface 27 against which the arcuate wire sealing member 28 rests. The inclined surface 27 and flat surface 26 together form a tapered groove whose width decreases as the radial distance from the rotor axis increases, and the wire 28 is of the same length as the root portion of the blade. This construction can also be seen at FIG. 4. The sealing members 28 are prevented from moving radially inwardly by means of a projecting portion 29 being provided upon the substantially flat surface 26, the projection 29 being spaced radially inward of that part of the flat surface 26 which corresponds with the inclined surface 27.
The sealing members and blades are prevented from moving axially from the disc by means of lock plates 30 and 31 shown in more detail at FIG. 3.
FIG. 6 shows a further embodiment of the invention, in this case the sealing member 28 is arranged to nestle in the tapered arcuate groove formed between two inclined arcuate step portions 32 provided upon the radially outermost surfaces of two recessed portions one of which is provided on each side of the blade root portion; again cooperating projections 33 radially inward of the surfaces 32 prevent the member 28 falling radially inwardly.
It will be readily understood that during operation of the turbine the centrifugal load imposed upon the sealing members 28 tend to force them radially outwards such that they are forced into the tapered section 27 of the recessed portion 25' (shown at FIG. 2) or between the two tapered portions 32 (shown at FIG. 6) thus providing an efficient sealing arrangement. The material of the wire will be chosen to have sufficient malleability to enable it to bed into the tapered groove. It will also be understood that the arcuate sealing members 28 also help damp out vibration occurring the blades, and by choosing seals of a particular size and weight, desired damping characteristics could be obtained.
Since the sealing members 28 are interposed between the platforms, they prevent these platforms fretting against one another, and their position at the inner end of the aerofoil enables them to provide damping of this area; clearly the faster the rotor rotates, the more centrifugal load acts on the sealing members and the greater will be the damping. It will also be understood that expansion or contraction occurring in the turbine may be accommodated by the above mentioned sealing arrangements.
It will also be appreciated that by producing seal members 28 in arcuate form the curved shape gives angular location to enable the ends of the seal member to be shaped by machining to conform with the surface of the blade front and rear faces 21a and 21b etc. The arcuate shape also prevents twisting of the seal member 28 and ensures friction damping.
It will be appreciated that whilst an embodiment of this invention has been described in connection with a turbine sealing device the invention is in no way restricted to such a device and could equally well be used for the sealing of a compressor rotor or similar device.
We claim:
1. A bladed rotor assembly for a gas turbine engine comprising a rotor and a plurality of angularly spaced apart aerofoil blades supported from the rotor, each blade having a platform member, said platform member having a face which cooperates with a corresponding face on the next adjacent blade to form a radially tapering groove whose width decreases as its distance from the rotor axis increases, said radially tapering groove being curved longitudinally relative said rotor assembly, and a sealing member mounted in the tapered and longitudinally curved groove so as to seal between the adjacent platforms, said sealing member comprising a wire curved longitudinally relative said rotor assembly and being substantially complementary to the longitudinal curve of said groove.
2. A bladed rotor assembly as claimed in claim 1 and in which there is at least one projection from one said face adapted to prevent said sealing member falling radially inward to disengage from said groove.
3. A bladed rotor assembly as claimed in claim 1 and in which there is a radially extending surface on one said face and an inclined surface on the cooperating face between which surfaces is formed said groove.
4. A bladed rotor assembly as claimed in claim 1 and in which there is an inclined surface on one said face and an oppositely inclined surface on the cooperating face between which surfaces is fonned said groove.
5. A bladed rotor assembly as claimed in claim 1 and comprising lock plates which engage between said rotor and said blades to limit axial movement of the blades and sealing members with respect to the rotor.
6. A bladed rotor assembly as claimed in claim 1 and in which said platforms comprise the root platforms of the blades.
7. A bladed rotor assembly as claimed in claim 1 and in which said platforms comprise the shroud platforms of the blades.

Claims (7)

1. A bladed rotor assembly for a gas turbine engine comprising a rotor and a plurality of angularly spaced apart aerofoil blades supported from the rotor, each blade having a platform member, said platform member having a face which cooperates with a corresponding face on the next adjacent blade to form a radially tapering groove whose width decreases as its distance from the rotor axis increases, said radially tapering groove being curved longitudinally relative said rotor assembly, and a sealing member mounted in the tapered and longitudinally curved groove so as to seal between the adjacent platforms, said sealing member comprising a wire curved longitudinally relative said rotor assembly and being substantially complementary to the longitudinal curve of said groove.
2. A bladed rotor assembly as claimed in claim 1 and in which there is at least one projection from one said face adapted to prevent said sealing member falling radially inward to disengage from said groove.
3. A bladed rotor assembly as claimed in claim 1 and in which there is a radially extending surface on one said face and an inclined surface on the cooperating face between which surfaces is formed said groove.
4. A bladed rotor assembly as claimed in claim 1 and in which there is an inclined surface on one said face and an oppositely inclined surface on the cooperating face between which surfaces is formed said groove.
5. A bladed rotor assembly as claimed in claim 1 and comprising lock plates which engage between said rotor and said blades to limit axial movement of the blades and sealing members with respect to the rotor.
6. A bladed rotor assembly as claimed in claim 1 and in which said platforms comprise the root platforms of the blades.
7. A bladed rotor assembly as claimed in claim 1 and in which said platforms comprise the shroud platforms of the blades.
US475916A 1973-06-26 1974-06-03 Blade assembly for a fluid flow machine Expired - Lifetime US3918842A (en)

Applications Claiming Priority (1)

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GB3025273A GB1460714A (en) 1973-06-26 1973-06-26 Bladed rotor for a gas turbine engine

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US3918842A true US3918842A (en) 1975-11-11

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JP (1) JPS5548166B2 (en)
FR (1) FR2235272B1 (en)
GB (1) GB1460714A (en)
IT (1) IT1012974B (en)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US4326835A (en) * 1979-10-29 1982-04-27 General Motors Corporation Blade platform seal for ceramic/metal rotor assembly
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US4936749A (en) * 1988-12-21 1990-06-26 General Electric Company Blade-to-blade vibration damper
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
EP1167691A2 (en) * 2000-06-30 2002-01-02 General Electric Company Blade damper and method for making same
US20040149163A1 (en) * 2003-02-03 2004-08-05 Taylor Fred J. Manual railroad hopper car door actuating mechanism
US20050047917A1 (en) * 2003-09-02 2005-03-03 Hans-Egon Brock Rotor of a steam or gas turbine
EP2053285A1 (en) * 2007-10-25 2009-04-29 Siemens Aktiengesellschaft Turbine blade assembly
WO2009053169A1 (en) * 2007-10-25 2009-04-30 Siemens Aktiengesellschaft Turbine blade assembly and seal strip
US20100111700A1 (en) * 2008-10-31 2010-05-06 Hyun Dong Kim Turbine blade including a seal pocket
US20110027088A1 (en) * 2009-07-31 2011-02-03 General Electric Company Rotor blades for turbine engines
US20120121384A1 (en) * 2010-11-15 2012-05-17 Mtu Aero Engines Gmbh Rotor and method for manufacturing a rotor for a turbo machine
US8393869B2 (en) 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
US20130323031A1 (en) * 2012-05-31 2013-12-05 Solar Turbines Incorporated Turbine damper
EP2679770A1 (en) 2012-06-26 2014-01-01 Siemens Aktiengesellschaft Platform seal strip for a gas turbine
US20150167480A1 (en) * 2012-06-15 2015-06-18 General Electric Company Methods and apparatus for sealing a gas turbine engine rotor assembly
US10385706B2 (en) * 2014-06-26 2019-08-20 Safran Aircraft Engines Rotary assembly for a turbomachine
US11352892B2 (en) 2020-04-17 2022-06-07 Raytheon Technologies Corporation Seal element for sealing a joint between a rotor blade and a rotor disk
FR3120903A1 (en) * 2021-03-16 2022-09-23 Safran Aircraft Engines Paddle wheel for a turbine
US11512602B2 (en) 2020-01-20 2022-11-29 Raytheon Technologies Corporation Seal element for sealing a joint between a rotor blade and a rotor disk

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GB8819133D0 (en) * 1988-08-11 1988-09-14 Rolls Royce Plc Bladed rotor assembly & sealing wire therefor
US6851932B2 (en) 2003-05-13 2005-02-08 General Electric Company Vibration damper assembly for the buckets of a turbine
EP2098687A1 (en) * 2008-03-07 2009-09-09 Siemens Aktiengesellschaft Rotor for a turbo engine
EP3438410B1 (en) 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine

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US3709631A (en) * 1971-03-18 1973-01-09 Caterpillar Tractor Co Turbine blade seal arrangement
US3752598A (en) * 1971-11-17 1973-08-14 United Aircraft Corp Segmented duct seal
US3834831A (en) * 1973-01-23 1974-09-10 Westinghouse Electric Corp Blade shank cooling arrangement

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US2445154A (en) * 1944-03-04 1948-07-13 Ingersoll Rand Co Blade mounting
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US3112915A (en) * 1961-12-22 1963-12-03 Gen Electric Rotor assembly air baffle
US3266770A (en) * 1961-12-22 1966-08-16 Gen Electric Turbomachine rotor assembly
US3709631A (en) * 1971-03-18 1973-01-09 Caterpillar Tractor Co Turbine blade seal arrangement
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Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US4326835A (en) * 1979-10-29 1982-04-27 General Motors Corporation Blade platform seal for ceramic/metal rotor assembly
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US4936749A (en) * 1988-12-21 1990-06-26 General Electric Company Blade-to-blade vibration damper
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
EP1167691A2 (en) * 2000-06-30 2002-01-02 General Electric Company Blade damper and method for making same
EP1167691A3 (en) * 2000-06-30 2003-10-15 General Electric Company Blade damper and method for making same
US20040149163A1 (en) * 2003-02-03 2004-08-05 Taylor Fred J. Manual railroad hopper car door actuating mechanism
US6955127B2 (en) 2003-02-03 2005-10-18 Taylor Fred J Manual railroad hopper car door actuating mechanism
US20050047917A1 (en) * 2003-09-02 2005-03-03 Hans-Egon Brock Rotor of a steam or gas turbine
US7104758B2 (en) * 2003-09-02 2006-09-12 Man Turbo Ag Rotor of a steam or gas turbine
CN101836018B (en) * 2007-10-25 2014-06-25 西门子公司 Turbine blade assembly and seal strip
US8613599B2 (en) 2007-10-25 2013-12-24 Siemens Aktiengesellschaft Turbine blade assembly and seal strip
US20110014050A1 (en) * 2007-10-25 2011-01-20 Peter Lake Turbine blade assembly and seal strip
WO2009053169A1 (en) * 2007-10-25 2009-04-30 Siemens Aktiengesellschaft Turbine blade assembly and seal strip
EP2053285A1 (en) * 2007-10-25 2009-04-29 Siemens Aktiengesellschaft Turbine blade assembly
RU2486349C2 (en) * 2007-10-25 2013-06-27 Сименс Акциенгезелльшафт Sealing ridge, assembly of turbine blades, and gas turbine containing such blade assembly
US20100111700A1 (en) * 2008-10-31 2010-05-06 Hyun Dong Kim Turbine blade including a seal pocket
CN102227545A (en) * 2008-10-31 2011-10-26 索拉透平公司 Turbine blade including seal pocket
US8137072B2 (en) 2008-10-31 2012-03-20 Solar Turbines Inc. Turbine blade including a seal pocket
US8393869B2 (en) 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
US8596983B2 (en) 2008-12-19 2013-12-03 Solar Turbines Inc. Turbine blade assembly including a damper
US20110027088A1 (en) * 2009-07-31 2011-02-03 General Electric Company Rotor blades for turbine engines
US8371816B2 (en) 2009-07-31 2013-02-12 General Electric Company Rotor blades for turbine engines
US9022727B2 (en) * 2010-11-15 2015-05-05 Mtu Aero Engines Gmbh Rotor for a turbo machine
US20120121384A1 (en) * 2010-11-15 2012-05-17 Mtu Aero Engines Gmbh Rotor and method for manufacturing a rotor for a turbo machine
US20120121436A1 (en) * 2010-11-15 2012-05-17 Mtu Aero Engines Gmbh Rotor for a turbo machine
US8888456B2 (en) * 2010-11-15 2014-11-18 Mtu Aero Engines Gmbh Rotor and method for manufacturing a rotor for a turbo machine
US9650901B2 (en) * 2012-05-31 2017-05-16 Solar Turbines Incorporated Turbine damper
US20130323031A1 (en) * 2012-05-31 2013-12-05 Solar Turbines Incorporated Turbine damper
US20150167480A1 (en) * 2012-06-15 2015-06-18 General Electric Company Methods and apparatus for sealing a gas turbine engine rotor assembly
US9840920B2 (en) * 2012-06-15 2017-12-12 General Electric Company Methods and apparatus for sealing a gas turbine engine rotor assembly
WO2014001084A1 (en) 2012-06-26 2014-01-03 Siemens Aktiengesellschaft Platform seal strip, turbine blade assembly and method for assembling it
EP2679770A1 (en) 2012-06-26 2014-01-01 Siemens Aktiengesellschaft Platform seal strip for a gas turbine
US10385706B2 (en) * 2014-06-26 2019-08-20 Safran Aircraft Engines Rotary assembly for a turbomachine
US11512602B2 (en) 2020-01-20 2022-11-29 Raytheon Technologies Corporation Seal element for sealing a joint between a rotor blade and a rotor disk
US11352892B2 (en) 2020-04-17 2022-06-07 Raytheon Technologies Corporation Seal element for sealing a joint between a rotor blade and a rotor disk
FR3120903A1 (en) * 2021-03-16 2022-09-23 Safran Aircraft Engines Paddle wheel for a turbine

Also Published As

Publication number Publication date
DE2430181A1 (en) 1975-01-16
DE2430181B2 (en) 1976-06-10
GB1460714A (en) 1977-01-06
FR2235272B1 (en) 1980-08-01
IT1012974B (en) 1977-03-10
JPS5069412A (en) 1975-06-10
JPS5548166B2 (en) 1980-12-04
FR2235272A1 (en) 1975-01-24

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