US20090136350A1 - Damping and sealing system for turbine blades - Google Patents

Damping and sealing system for turbine blades Download PDF

Info

Publication number
US20090136350A1
US20090136350A1 US11/896,508 US89650807A US2009136350A1 US 20090136350 A1 US20090136350 A1 US 20090136350A1 US 89650807 A US89650807 A US 89650807A US 2009136350 A1 US2009136350 A1 US 2009136350A1
Authority
US
United States
Prior art keywords
sealing
damping
damping element
sealing system
rubbing
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.)
Abandoned
Application number
US11/896,508
Inventor
Richard Whitton
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Assigned to ROLLS-ROYCE DEUTSCHLAND LTD & CO KG reassignment ROLLS-ROYCE DEUTSCHLAND LTD & CO KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WHITTON, RICHARD
Publication of US20090136350A1 publication Critical patent/US20090136350A1/en
Abandoned 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
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • This invention relates to a damping and sealing system for turbine blades with a sealing and damping element generally in the form of a straight three sided prism with equal sides which, by centrifugal effect, is retained between opposite faces of adjacent platforms of the blades fitted to the rotor of a gas-turbine engine.
  • Gas-turbine engines feature rotor disks with radially extending blades, having a blade root, a platform and an airfoil, mounted on the periphery of the rotor disks.
  • rotor disks with radially extending blades, having a blade root, a platform and an airfoil, mounted on the periphery of the rotor disks.
  • Sealing elements arranged between the blade platforms have been long known, whose cross-section is complementary to the shape of the space remaining between the platforms and which must be installed in this space in a specific orientation. Assembly is accordingly time-consuming and costly, and incorrect orientation of the sealing element considerably affects its sealing and damping efficiency. Moreover, the closely matched form of sealing element and platform gap requires considerable production effort.
  • U.S. Pat. No. 4,872,812 proposes a sealing and damping element with planar sides arranged about its longitudinal axis, with the cross-section of this sealing and damping element being an equilateral triangle.
  • the regular cross-section of the sealing and damping element enables two each of its surfaces, irrespective of the orientation with which the element is assembled, to be driven into engagement with the respective edges of the adjacent platforms to seal the gap and dampen the vibrations of the respective blades when acted upon by centrifugal force.
  • High sealing and damping efficiency requires, however, close production tolerances and, thus high production effort with regard to the planar form of the mating surfaces on both sides.
  • the sealing and damping efficiency can be affected by wear to the planar mating surfaces.
  • sealing and damping elements with circular cross-section have been proposed which, in any orientation, mate with the side edges of the two adjacent platforms when acted upon by centrifugal force. It was found, however, that round sealing and damping elements wear quite rapidly, as a result of which the sealing and damping efficiency is affected and the sealing and damping elements have to be replaced with considerable effort.
  • the present invention provides a sealing and damping system for turbine blades, which is characterized by a high sealing and damping efficiency, while requiring only low assembly and repair effort.
  • the present invention provides a sealing and damping element in the form of a straight three sided prism with convex sides allowing the sealing and damping element to perform a slight swiveling movement in operation and thus acting as enlarged rubbing surfaces.
  • the increased friction thus obtained results in improved vibration damping.
  • Rubbing wear leads to a mutual conditioning of the contacting mating surfaces.
  • production tolerances are leveled out and vibration damping and sealing efficiency is further improved.
  • Production inaccuracies are compensated for by the automatic, mutual conditioning of the sealing or rubbing surfaces. Rubbing wear can be taken into account in the design. Therefore, the production and repair effort is low.
  • the opposite sealing surfaces of the adjacent blade platforms form an acute-angled gap into which the sealing and damping element is automatically forced by the action of centrifugal force, contacting the gap surfaces with two curved rubbing surfaces.
  • FIG. 1 is a partial view of a gas turbine with a turbine blade attached to a rotor disk
  • FIG. 2 is a section AA as per FIG. 1 with a sealing and damping element arranged between two blades.
  • a rotor 2 is disposed between two stator vanes 1 spaced in flow direction, with turbine blades 4 arranged on the periphery of a rotor disk 3 , which includes a blade root 5 , a blade platform 6 and an airfoil 7 .
  • the detailed representation in FIG. 2 shows two adjoining platforms 6 a , 6 b of adjacent turbine blades 4 .
  • the platform 6 a shown on the right-hand side of the drawing, features a recess 8 in which a sealing and damping element 9 is loosely received.
  • the recess 8 Positioned opposite to the open side of the recess 8 —with a very small gap 10 left—is a planar, essentially vertical platform edge 11 of the other platform 6 b which prevents the sealing and damping element 9 from falling out of the recess 8 .
  • the recess 8 has a sealing surface 12 which extends obliquely upwards.
  • the sealing and damping element 9 is a straight component with the cross-section generally of an equilateral triangle, however with rounded longitudinal edges 13 and with convex—crowned—rubbing surfaces 14 (sealing and damping faces, side faces) between the longitudinal edges 13 .
  • One of the edges 13 faces generally upward, as shown in FIG. 2 .
  • the sealing and damping element 9 is loose in the recess 8 at rest. During rotation of the rotor 2 , however, centrifugal force acts on the sealing and damping element 9 so that its respective convex rubbing surfaces 14 abut the vertical platform edge 11 and the oblique sealing surface 12 . Rotation of the sealing and damping element 9 about its longitudinal axis is thus counteracted.
  • the curvature and the rotationally symmetric arrangement of the curved rubbing surfaces 14 about a longitudinal axis allow the sealing and damping element 9 to perform a slight swiveling movement about the longitudinal axis, in consequence of which the curved rubbing surfaces 14 are conditioned, and slightly flattened, by wear in the areas of contact with the platform edge 11 and the oblique sealing surface 12 , so that the actual area of rub is increased and adapted to the platform design, and geometrical differences caused by the production process are leveled out.
  • the slight swiveling movement which the sealing and dampening element is allowed to perform enlarges the area of rub and increases friction.

Abstract

With a gas-turbine engine, a sealing and damping element (9), which is loosely held between two adjacent platforms (6 a , 6 b) of turbine blades attached to a rotor disk, generally has a cross-section in the form of a straight three sided prism corresponding to an equilateral triangle, however with convex rubbing surface sides. Due to small swiveling movements enabled by the curvature of the sides, an increased rubbing and wear area is created during operation, which is adapted to the blade geometry and can be determined in advance, thus increasing damping and sealing efficiency.

Description

  • This application claims priority to German Patent Application DE 10 2006 041 322.9 filed Sep. 1, 2006, the entirety of which is incorporated by reference herein.
  • This invention relates to a damping and sealing system for turbine blades with a sealing and damping element generally in the form of a straight three sided prism with equal sides which, by centrifugal effect, is retained between opposite faces of adjacent platforms of the blades fitted to the rotor of a gas-turbine engine.
  • Gas-turbine engines feature rotor disks with radially extending blades, having a blade root, a platform and an airfoil, mounted on the periphery of the rotor disks. On the one hand, there is a need to seal the narrow gap remaining between adjoining edges of adjacent platforms to minimize gas exchange between hot gas and cooling air; on the other hand, it is necessary to dampen the vibrations between the rotor disk and the blades, as well as between the blades themselves.
  • Sealing elements arranged between the blade platforms have been long known, whose cross-section is complementary to the shape of the space remaining between the platforms and which must be installed in this space in a specific orientation. Assembly is accordingly time-consuming and costly, and incorrect orientation of the sealing element considerably affects its sealing and damping efficiency. Moreover, the closely matched form of sealing element and platform gap requires considerable production effort.
  • For one solution to this problem, Specification U.S. Pat. No. 4,872,812 proposes a sealing and damping element with planar sides arranged about its longitudinal axis, with the cross-section of this sealing and damping element being an equilateral triangle. The regular cross-section of the sealing and damping element enables two each of its surfaces, irrespective of the orientation with which the element is assembled, to be driven into engagement with the respective edges of the adjacent platforms to seal the gap and dampen the vibrations of the respective blades when acted upon by centrifugal force. High sealing and damping efficiency requires, however, close production tolerances and, thus high production effort with regard to the planar form of the mating surfaces on both sides. Moreover, the sealing and damping efficiency can be affected by wear to the planar mating surfaces.
  • In order to reduce the production and assembly effort, sealing and damping elements with circular cross-section have been proposed which, in any orientation, mate with the side edges of the two adjacent platforms when acted upon by centrifugal force. It was found, however, that round sealing and damping elements wear quite rapidly, as a result of which the sealing and damping efficiency is affected and the sealing and damping elements have to be replaced with considerable effort.
  • In a broad aspect, the present invention provides a sealing and damping system for turbine blades, which is characterized by a high sealing and damping efficiency, while requiring only low assembly and repair effort.
  • It is a particular object of the present invention to provide at least one solution to the above problems by a sealing and damping system designed in accordance with the features described herein. Advantageous developments of the present invention become apparent from the present description.
  • The present invention provides a sealing and damping element in the form of a straight three sided prism with convex sides allowing the sealing and damping element to perform a slight swiveling movement in operation and thus acting as enlarged rubbing surfaces. The increased friction thus obtained results in improved vibration damping. Rubbing wear leads to a mutual conditioning of the contacting mating surfaces. Thus, production tolerances are leveled out and vibration damping and sealing efficiency is further improved. Production inaccuracies are compensated for by the automatic, mutual conditioning of the sealing or rubbing surfaces. Rubbing wear can be taken into account in the design. Therefore, the production and repair effort is low.
  • The opposite sealing surfaces of the adjacent blade platforms form an acute-angled gap into which the sealing and damping element is automatically forced by the action of centrifugal force, contacting the gap surfaces with two curved rubbing surfaces.
  • The present invention is more fully described in light of the accompanying drawings. In the drawings,
  • FIG. 1 is a partial view of a gas turbine with a turbine blade attached to a rotor disk, and
  • FIG. 2 is a section AA as per FIG. 1 with a sealing and damping element arranged between two blades.
    •
  • As can be seen from FIG. 1, a rotor 2 is disposed between two stator vanes 1 spaced in flow direction, with turbine blades 4 arranged on the periphery of a rotor disk 3, which includes a blade root 5, a blade platform 6 and an airfoil 7. The detailed representation in FIG. 2 shows two adjoining platforms 6 a, 6 b of adjacent turbine blades 4. The platform 6 a, shown on the right-hand side of the drawing, features a recess 8 in which a sealing and damping element 9 is loosely received. Positioned opposite to the open side of the recess 8—with a very small gap 10 left—is a planar, essentially vertical platform edge 11 of the other platform 6 b which prevents the sealing and damping element 9 from falling out of the recess 8. The recess 8 has a sealing surface 12 which extends obliquely upwards. The sealing and damping element 9 is a straight component with the cross-section generally of an equilateral triangle, however with rounded longitudinal edges 13 and with convex—crowned—rubbing surfaces 14 (sealing and damping faces, side faces) between the longitudinal edges 13. One of the edges 13 faces generally upward, as shown in FIG. 2.
  • The sealing and damping element 9 is loose in the recess 8 at rest. During rotation of the rotor 2, however, centrifugal force acts on the sealing and damping element 9 so that its respective convex rubbing surfaces 14 abut the vertical platform edge 11 and the oblique sealing surface 12. Rotation of the sealing and damping element 9 about its longitudinal axis is thus counteracted. However, the curvature and the rotationally symmetric arrangement of the curved rubbing surfaces 14 about a longitudinal axis allow the sealing and damping element 9 to perform a slight swiveling movement about the longitudinal axis, in consequence of which the curved rubbing surfaces 14 are conditioned, and slightly flattened, by wear in the areas of contact with the platform edge 11 and the oblique sealing surface 12, so that the actual area of rub is increased and adapted to the platform design, and geometrical differences caused by the production process are leveled out. In addition, the slight swiveling movement which the sealing and dampening element is allowed to perform enlarges the area of rub and increases friction. The deliberately effected wear due to friction of the curved rubbing surfaces 14 and the mating surfaces with the two opposite platforms is determinable in advance, and is accounted for in the blade design. By interaction of the above effects, an optimum rubbing surface is provided and, due to high friction, maximum damping and, ultimately, improved sealing efficiency achieved, but with the sealing and damping element being prevented from uncontrolled or premature wear by permanent rotation. The production and repair effort is reduced.
    • LIST OF REFERENCE NUMERALS
    • 1 Stator vane
    • 2 Rotor
    • 3 Rotor disk
    • 4 Turbine blades
    • 5 Blade root
    • 6 Platform
    • 6 a Right-hand platform
    • 6 b Left-hand platform
    • 7 Airfoil
    • 8 Recess
    • 9 Sealing and damping element
    • 10 Gap
    • 11 Straight, vertical platform edge
    • 12 Oblique sealing surface
    • 13 Rounded longitudinal edges
    • 14 Rubbing surface, curved side face

Claims (6)

1. A damping and sealing system for turbine blades of a gas-turbine engine, comprising:
a sealing and damping element generally in the form of a straight three sided prism with equal side faces which, by centrifugal effect during operation of the gas-turbine engine, is retained between opposing surfaces of adjacent platforms of the blades fitted to a rotor of the gas-turbine engine, wherein the side faces of the sealing and damping element are configured as convex rubbing surfaces to allow for a slight swiveling movement of the rubbing surfaces with respect to the opposing surfaces of the adjacent blade platforms to thereby increase rubbing efficiency.
2. A damping and sealing system in accordance with claim 1, wherein the opposing surfaces of the adjacent platforms form a wedge-shaped, acute-angled gap, in which the sealing and damping element is loosely fixed.
3. A damping and sealing system in accordance with claim 2, wherein the gap is formed by a generally straight platform edge of the one platform and by an oblique sealing surface in a recess of the other platform.
4. A damping and sealing system in accordance with claim 3, wherein the gap surfaces in the rubbing/wear area of the sealing and damping element are dimensioned in a manner commensurate with an amount of wear expected.
5. A damping and sealing system in accordance with claim 4, wherein longitudinal edges of the sealing and damping element are rounded.
6. A damping and sealing system in accordance with claim 1, wherein longitudinal edges of the sealing and damping element are rounded.
US11/896,508 2006-09-01 2007-09-04 Damping and sealing system for turbine blades Abandoned US20090136350A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006041322.9 2006-09-01
DE102006041322A DE102006041322A1 (en) 2006-09-01 2006-09-01 Damping and sealing system for turbine blades

Publications (1)

Publication Number Publication Date
US20090136350A1 true US20090136350A1 (en) 2009-05-28

Family

ID=38969468

Family Applications (1)

Application Number Title Priority Date Filing Date
US11/896,508 Abandoned US20090136350A1 (en) 2006-09-01 2007-09-04 Damping and sealing system for turbine blades

Country Status (3)

Country Link
US (1) US20090136350A1 (en)
EP (1) EP1898050B1 (en)
DE (1) DE102006041322A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2961845A1 (en) * 2010-06-28 2011-12-30 Snecma Propulsion Solide TURBOMACHINE DAWN WITH COMPLEMENTARY PAIRE / IMPAIRE GEOMETRY AND METHOD OF MANUFACTURING THE SAME
US9045992B2 (en) 2010-06-28 2015-06-02 Herakles Turbomachine blades or vanes having complementary even/odd geometry
US9810075B2 (en) 2015-03-20 2017-11-07 United Technologies Corporation Faceted turbine blade damper-seal

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010052965B4 (en) 2010-11-30 2014-06-12 MTU Aero Engines AG Damping means for damping a blade movement of a turbomachine

Citations (14)

* 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
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4537024A (en) * 1979-04-23 1985-08-27 Solar Turbines, Incorporated Turbine engines
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US5156528A (en) * 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
US5730584A (en) * 1996-05-09 1998-03-24 Rolls-Royce Plc Vibration damping
US5749705A (en) * 1996-10-11 1998-05-12 General Electric Company Retention system for bar-type damper of rotor blade
US6086329A (en) * 1997-03-12 2000-07-11 Mitsubishi Heavy Industries, Ltd. Seal plate for a gas turbine moving blade
US6450769B2 (en) * 2000-03-22 2002-09-17 Alstom (Switzerland) Ltd Blade assembly with damping elements
US6478544B2 (en) * 2000-05-08 2002-11-12 Alstom (Switzerland) Ltd Blade arrangement with damping elements
US20040228731A1 (en) * 2003-05-13 2004-11-18 Lagrange Benjamin Arnette Vibration damper assembly for the buckets of a turbine
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same
US7534090B2 (en) * 2006-06-13 2009-05-19 General Electric Company Enhanced bucket vibration system

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1177367B1 (en) * 1999-05-12 2003-08-20 Siemens Aktiengesellschaft Seal for sealing a gap, in particular in a turbine, and a turbine

Patent Citations (15)

* 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
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4537024A (en) * 1979-04-23 1985-08-27 Solar Turbines, Incorporated Turbine engines
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
US5156528A (en) * 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
US5730584A (en) * 1996-05-09 1998-03-24 Rolls-Royce Plc Vibration damping
US5749705A (en) * 1996-10-11 1998-05-12 General Electric Company Retention system for bar-type damper of rotor blade
US6086329A (en) * 1997-03-12 2000-07-11 Mitsubishi Heavy Industries, Ltd. Seal plate for a gas turbine moving blade
US6450769B2 (en) * 2000-03-22 2002-09-17 Alstom (Switzerland) Ltd Blade assembly with damping elements
US6478544B2 (en) * 2000-05-08 2002-11-12 Alstom (Switzerland) Ltd Blade arrangement with damping elements
US20040228731A1 (en) * 2003-05-13 2004-11-18 Lagrange Benjamin Arnette Vibration damper assembly for the buckets of a turbine
US6851932B2 (en) * 2003-05-13 2005-02-08 General Electric Company Vibration damper assembly for the buckets of a turbine
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same
US7534090B2 (en) * 2006-06-13 2009-05-19 General Electric Company Enhanced bucket vibration system

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2961845A1 (en) * 2010-06-28 2011-12-30 Snecma Propulsion Solide TURBOMACHINE DAWN WITH COMPLEMENTARY PAIRE / IMPAIRE GEOMETRY AND METHOD OF MANUFACTURING THE SAME
WO2012001278A1 (en) * 2010-06-28 2012-01-05 Snecma Propulsion Solide Turbomachine blade having an even/odd complementary geometry and its manufacturing process
CN102958680A (en) * 2010-06-28 2013-03-06 赫拉克勒斯公司 Turbomachine blade having even/odd complementary geometry and manufacturing process thereof
JP2013532257A (en) * 2010-06-28 2013-08-15 ヘラクレス Turbomachine blades having complementary even / odd geometry and method of manufacturing the same
US9045992B2 (en) 2010-06-28 2015-06-02 Herakles Turbomachine blades or vanes having complementary even/odd geometry
US9810075B2 (en) 2015-03-20 2017-11-07 United Technologies Corporation Faceted turbine blade damper-seal

Also Published As

Publication number Publication date
EP1898050A2 (en) 2008-03-12
EP1898050A3 (en) 2010-07-07
DE102006041322A1 (en) 2008-04-24
EP1898050B1 (en) 2011-09-07

Similar Documents

Publication Publication Date Title
CN101529052B (en) Turbine blade assembly
JP7034587B2 (en) Turbine rotor blade with shroud
EP2149674B1 (en) Bladed turbine rotor with vibration damper
US8105041B2 (en) Arrangement for axially securing rotating blades in a rotor, sealing element for such an arrangement, and use of such an arrangement
US6916021B2 (en) Sealing arrangement
RU2456460C2 (en) System to prevent wear of tip airfoil shroud platform of turbine blade
US8790086B2 (en) Turbine blade assembly for retaining sealing and dampening elements
US7001152B2 (en) Shrouded turbine blades with locally increased contact faces
JP6866145B2 (en) Turbine rotor blade with shroud
US10287895B2 (en) Midspan shrouded turbine rotor blades
EP2163725B1 (en) Turbine blade damper arrangement
US9347325B2 (en) Damper for a turbine rotor assembly
US9145788B2 (en) Retrofittable interstage angled seal
US9303519B2 (en) Damper for a turbine rotor assembly
US9297263B2 (en) Turbine blade for a gas turbine engine
US20170183971A1 (en) Tip shrouded turbine rotor blades
CN102536331A (en) Turbine blade combined damper and sealing pin and related method
CN102588001A (en) Damper coverplate and sealing arrangement for turbine bucket shank
CN205743992U (en) Gas turbine including the flow passage with rotor assembly
US20140119943A1 (en) Turbine rotor assembly
CN105909315A (en) Turbine rotor blade
KR20100080451A (en) Turbine blade root configurations
JP6669484B2 (en) Channel boundaries and rotor assemblies in gas turbines
US20090136350A1 (en) Damping and sealing system for turbine blades
US20160108737A1 (en) Blade system, and corresponding method of manufacturing a blade system

Legal Events

Date Code Title Description
AS Assignment

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:WHITTON, RICHARD;REEL/FRAME:019837/0379

Effective date: 20070828

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION