WO2008046684A1 - Turbine blade assembly - Google Patents

Turbine blade assembly Download PDF

Info

Publication number
WO2008046684A1
WO2008046684A1 PCT/EP2007/059084 EP2007059084W WO2008046684A1 WO 2008046684 A1 WO2008046684 A1 WO 2008046684A1 EP 2007059084 W EP2007059084 W EP 2007059084W WO 2008046684 A1 WO2008046684 A1 WO 2008046684A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
turbine blades
platforms
seal
blades
Prior art date
Application number
PCT/EP2007/059084
Other languages
French (fr)
Inventor
Scott Charlton
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP07803092A priority Critical patent/EP2054588B1/en
Priority to US12/311,837 priority patent/US8545181B2/en
Priority to CN2007800387455A priority patent/CN101529054B/en
Priority to ES07803092T priority patent/ES2391419T3/en
Publication of WO2008046684A1 publication Critical patent/WO2008046684A1/en

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
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a turbine blade assembly, in par ⁇ ticular for a gas turbine and a method for assembling a turbine blade assembly.
  • Seal strips are used between adjacent turbine blades to pre ⁇ vent the ingress of hot gasses into a root cavity which can cause undesired heating of the disc rim and loss of effi ⁇ ciency.
  • seal strips cannot be introduced using the conventional sequential build methodology. More so a method must be devised to permit as ⁇ sembly and retention of the strips with the bladed disc com- plete.
  • EP 1 600 606 Al discloses an arrangement of turbine blades with gaps between the platforms of adjacent turbine blades. These gaps are closed by sealing and damping elements in the form of strips. The sealing and damping strips are held in place by centrifugal forces.
  • the objective of the invention is to provide an improved tur ⁇ bine blade assembly with a seal strip. Another objective is to provide a gas turbine with an improved turbine blade as ⁇ sembly comprising a seal strip. A third objective of the in- vention is to provide an improved method for assembling a turbine blade assembly with a seal strip.
  • An inventive turbine blade assembly comprises turbine blades with platforms and gaps between the platforms of adjacent turbine blades. It further comprises seals. Each seal cov ⁇ ers the gap between the platforms of two adjacent turbine blades.
  • the platforms are provided with slots in circumfer ⁇ ential sides facing adjacent turbine blades, and the turbine blades comprise root cavities, wherein the seal covers at least the whole length of the root cavities of two adjacent turbine blades.
  • the seal is formed from a strip and is placed in two opposed slots formed in each of the platforms of two adjacent turbine blades, and being open towards their down ⁇ stream ends .
  • This arrangement provides a sealing between adjacent turbine blades.
  • the seal prevents the ingress of hot gases into the root cavity which can cause undesired heating of the disc rim and loss of efficiency.
  • the form of the strip ensures full cavity sealing results across the length of the platform and prevents the ingress of hot gases.
  • the seal strips are placed in opposed slots formed in each of the platforms of two adjacent turbine blades. This allows for precise posi ⁇ tioning of the seal strips.
  • the seal is made of a flexi ⁇ ble, resilient material.
  • the material permits the strips to be inserted into the slots from the open downstream end using a continuous motion.
  • the seal is locked in the blades by locking plates which are assembled at the downstream end of the turbine disc.
  • the locking plates are used for both blade retention and to prevent cross leakage of cooling air.
  • the seal is retained in a slot cavity at the upstream end with an appropriate gap to allow for transient thermal growths - this ensures no forced damping of the blade during operation.
  • a gas turbine may be equipped with a turbine blade assembly according to the present invention.
  • the gas turbine will have a reduced loss of cooling air and heating of the turbine disc rim.
  • the invention further comprises a method for assembling a turbine blade assembly, in particular for a gas turbine, wherein turbine blades are assembled to a turbine disc and seals are assembled to platforms of platform blades to cover gaps between the platforms of adjacent turbine blades. All the turbine blades are fitted to the turbine disc before the seals are fitted between the platforms of adjacent turbine blades.
  • the form of the strips and the method of retention permits the strips to be fitted to a bladed disc assembly where all the blades have previously been fitted.
  • the seals can be fitted from the downstream bladed disc face. This allows for an easier assembly and disassembly.
  • the seals may be inserted into opposing slots in adjacent platforms by continuous motion permitting an easy assembly.
  • Figure 1 shows a turbine blade with a slot.
  • Figure 2 shows a seal strip
  • Figure 3 shows a turbine blade with an inserted seal strip.
  • Figure 1 shows a side view of a turbine blade 2 with a air ⁇ foil 3, a platform 4, a blade root 5, a root cavity 6 and a slot 8.
  • the platform 4 is placed at the bottom of the airfoil 3 and covers the root cavity 6 that is formed between the blade root 5 and the platform 4.
  • a slot 8 is integrated into each side of the platform 4 running along the top of the root cavity 6.
  • the turbine blade 2 is used in a gas turbine where hot pres ⁇ surized gas is guided towards turbine blades with airfoils that are fixed on a rotor to move the turbine blades and thus drive the rotor to which the turbine blades are assembled in a circumferential direction. Due to the contact of the tur ⁇ bine blades with the hot gas a cooling of the turbine blades is required. Cooling air is guided through the blade roots 5 of the turbine blades 2 into the airfoils 3.
  • Figure 2 shows a seal strip 10 according to the invention.
  • the seal strip 10 is a stretched rectangular shaped, skewed in line with the blade roots with rounded corners for better insertion. It is made of a flexible, resilient material for better assembly and disassembly.
  • the seal strip 10 preformed as per figure 2b prior to insertion, this enables fitting us ⁇ ing a continuous action from the downstream face of the turbine blade 2 into the slot 8.
  • Figure 3 shows a turbine blade 2 as shown in Figure 1 mounted to a turbine disc 12 by insertion of its blade root 5 into an axial groove 13 of the turbine disc 12.
  • the axial grooves 13 run along the circumference of the turbine disc 12.
  • the ax- ial grooves 13 are formed to hold the roots 5 of the turbine blades 2.
  • Several turbine discs 12 form the rotor of the gas turbine (not shown) . After the turbine blades 2 are assem ⁇ bled to the turbine disc 12 to form a full ring seal strips 10 are fitted in the opposed slots 8 of adjacent turbine blades 2 from their downstream end by a continuous motion.
  • hot gas passes the airfoil 3 of the turbine blade 2 causing a rotation of the turbine blade 2. Cooling air is passed through the blade root 5 into the airfoil 3 to cool the turbine blade 2.
  • the seal 10 keeps cooling air under the platforms 4 of adjacent turbine blades 2 and prevents hot gas from flowing into the root cavity 6 of the turbine blade 2. This prevents overheating of disc rim 12 ensuring safe turbine operation.
  • the seal strip 10 is made of a flexible, resilient material so that it is held in the slot 8 by its resilient force. It is also retained in the slot 8 by a force fit in the upstream end of the slot 8. The seal 10 is inserted from the down ⁇ stream end of the slot 8.
  • Each stage of the turbine is assembled by fitting turbine blades 2 to a turbine disc 12 to complete a full ring. After that the seal strips 10 are fitted in the opposed slots 8 of adjacent turbine blades 2 from their downstream end by a con ⁇ tinuous motion.

Landscapes

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

Abstract

A turbine blade assembly, in particular for a gas turbine, comprising turbine blades (2) with platforms (4), gaps between the platforms (4) of adjacent turbine blades (2) and seals (10), each seal (10) covers the gap between the platforms (4) of two adjacent turbine blades (2) wherein the platforms are provided with slots extending in flow direction, the turbine blades (2) comprising root cavities (6), wherein the seal (10) covers at least the whole length of the root cavities (6) of two adjacent turbine blades (2), the seal is formed from a strip (10) and the seal (10) is placed in two opposed slots (8) formed in each of the platforms (4) of two adjacent turbine blades (2) and open towards their downstream ends.

Description

Description
Turbine blade assembly
Background of the invention
The invention relates to a turbine blade assembly, in par¬ ticular for a gas turbine and a method for assembling a turbine blade assembly.
Seal strips are used between adjacent turbine blades to pre¬ vent the ingress of hot gasses into a root cavity which can cause undesired heating of the disc rim and loss of effi¬ ciency. Where blades are assembled into the disc as a full ring (for interlocked designs or where differential plat¬ form/root and shroud skew angles are in evidence) seal strips cannot be introduced using the conventional sequential build methodology. More so a method must be devised to permit as¬ sembly and retention of the strips with the bladed disc com- plete.
Generally assemblies have been built up using sequential build techniques where single blades and strips are assembled to complete the full ring. Where blades are fitted as full sets then full length platform seal strips have not been utilised. In previous cases small seal plates have been fit¬ ted in upstream seal slots and retained using locking strips. This does not provide adequate coverage across the platform length in addition that seal strips are not used in high pressure turbine disc assemblies as locking plates are re¬ quired for both blade retention and to prevent cross leakage of cooling air. This state of the art does not provide an adequate measure for preventing ingress of hot gas into the root cavities of the turbine blades.
EP 1 600 606 Al discloses an arrangement of turbine blades with gaps between the platforms of adjacent turbine blades. These gaps are closed by sealing and damping elements in the form of strips. The sealing and damping strips are held in place by centrifugal forces.
Document US 4,265,594 discloses a turbine blade arrangement with turbine blades having platforms with segments and cover plates extending in the longitudinal direction of the rotor axis . The gaps between the cover plates are provided with slots in which sealing strips are inserted.
Sealing arrangements for turbine vanes are described in GB 2 280 935 A, GB 1 580 884, WO 2004/074640 Al, GB 2 303 888 A, GB 2 182 399 A and JP 10184310 A.
Objective of the invention
The objective of the invention is to provide an improved tur¬ bine blade assembly with a seal strip. Another objective is to provide a gas turbine with an improved turbine blade as¬ sembly comprising a seal strip. A third objective of the in- vention is to provide an improved method for assembling a turbine blade assembly with a seal strip.
Solution according to the invention
These objectives are solved by a turbine blade assembly with the features of claim 1, by a gas turbine according to claim 5 and by a method for assembling a turbine blade assembly ac¬ cording to claim 6. The depending claims contain further developments of the invention.
An inventive turbine blade assembly comprises turbine blades with platforms and gaps between the platforms of adjacent turbine blades. It further comprises seals. Each seal cov¬ ers the gap between the platforms of two adjacent turbine blades. The platforms are provided with slots in circumfer¬ ential sides facing adjacent turbine blades, and the turbine blades comprise root cavities, wherein the seal covers at least the whole length of the root cavities of two adjacent turbine blades. The seal is formed from a strip and is placed in two opposed slots formed in each of the platforms of two adjacent turbine blades, and being open towards their down¬ stream ends .
This arrangement provides a sealing between adjacent turbine blades. The seal prevents the ingress of hot gases into the root cavity which can cause undesired heating of the disc rim and loss of efficiency. The form of the strip ensures full cavity sealing results across the length of the platform and prevents the ingress of hot gases. The seal strips are placed in opposed slots formed in each of the platforms of two adjacent turbine blades. This allows for precise posi¬ tioning of the seal strips.
In an advantageous development the seal is made of a flexi¬ ble, resilient material. The material permits the strips to be inserted into the slots from the open downstream end using a continuous motion.
In another advantageous development of the invention the seal is locked in the blades by locking plates which are assembled at the downstream end of the turbine disc. The locking plates are used for both blade retention and to prevent cross leakage of cooling air.
The seal is retained in a slot cavity at the upstream end with an appropriate gap to allow for transient thermal growths - this ensures no forced damping of the blade during operation.
Advantageously a gas turbine may be equipped with a turbine blade assembly according to the present invention. The gas turbine will have a reduced loss of cooling air and heating of the turbine disc rim.
The invention further comprises a method for assembling a turbine blade assembly, in particular for a gas turbine, wherein turbine blades are assembled to a turbine disc and seals are assembled to platforms of platform blades to cover gaps between the platforms of adjacent turbine blades. All the turbine blades are fitted to the turbine disc before the seals are fitted between the platforms of adjacent turbine blades. The form of the strips and the method of retention permits the strips to be fitted to a bladed disc assembly where all the blades have previously been fitted.
The seals can be fitted from the downstream bladed disc face. This allows for an easier assembly and disassembly.
The seals may be inserted into opposing slots in adjacent platforms by continuous motion permitting an easy assembly.
Further features, characteristics and advantages of the in¬ vention become clear from the following description of the embodiments in reference to the accompanying drawings.
Brief description of the drawings
Figure 1 shows a turbine blade with a slot.
Figure 2 shows a seal strip.
Figure 3 shows a turbine blade with an inserted seal strip.
Detailed description of the embodiment
Figure 1 shows a side view of a turbine blade 2 with a air¬ foil 3, a platform 4, a blade root 5, a root cavity 6 and a slot 8.
The platform 4 is placed at the bottom of the airfoil 3 and covers the root cavity 6 that is formed between the blade root 5 and the platform 4. A slot 8 is integrated into each side of the platform 4 running along the top of the root cavity 6. When assembled to a turbine disc 12 two slots 8 of two adjacent turbine blades 2 are in an opposed position to hold a seal strip 10 from two sides. The slots 8 are closed towards the upstream end for retention and open towards the downstream end of the turbine blade 2 for insertion. Each two opposed slots 8 are provided as guides and retentions of a seal strip 10.
The turbine blade 2 is used in a gas turbine where hot pres¬ surized gas is guided towards turbine blades with airfoils that are fixed on a rotor to move the turbine blades and thus drive the rotor to which the turbine blades are assembled in a circumferential direction. Due to the contact of the tur¬ bine blades with the hot gas a cooling of the turbine blades is required. Cooling air is guided through the blade roots 5 of the turbine blades 2 into the airfoils 3.
Figure 2 shows a seal strip 10 according to the invention. The seal strip 10 is a stretched rectangular shaped, skewed in line with the blade roots with rounded corners for better insertion. It is made of a flexible, resilient material for better assembly and disassembly. The seal strip 10 preformed as per figure 2b prior to insertion, this enables fitting us¬ ing a continuous action from the downstream face of the turbine blade 2 into the slot 8.
Figure 3 shows a turbine blade 2 as shown in Figure 1 mounted to a turbine disc 12 by insertion of its blade root 5 into an axial groove 13 of the turbine disc 12. The axial grooves 13 run along the circumference of the turbine disc 12. The ax- ial grooves 13 are formed to hold the roots 5 of the turbine blades 2. Several turbine discs 12 form the rotor of the gas turbine (not shown) . After the turbine blades 2 are assem¬ bled to the turbine disc 12 to form a full ring seal strips 10 are fitted in the opposed slots 8 of adjacent turbine blades 2 from their downstream end by a continuous motion.
In operation of the gas turbine, hot gas passes the airfoil 3 of the turbine blade 2 causing a rotation of the turbine blade 2. Cooling air is passed through the blade root 5 into the airfoil 3 to cool the turbine blade 2. The seal 10 keeps cooling air under the platforms 4 of adjacent turbine blades 2 and prevents hot gas from flowing into the root cavity 6 of the turbine blade 2. This prevents overheating of disc rim 12 ensuring safe turbine operation.
The seal strip 10 is made of a flexible, resilient material so that it is held in the slot 8 by its resilient force. It is also retained in the slot 8 by a force fit in the upstream end of the slot 8. The seal 10 is inserted from the down¬ stream end of the slot 8.
Each stage of the turbine is assembled by fitting turbine blades 2 to a turbine disc 12 to complete a full ring. After that the seal strips 10 are fitted in the opposed slots 8 of adjacent turbine blades 2 from their downstream end by a con¬ tinuous motion.

Claims

Claims
1. A turbine blade assembly, in particular for a gas turbine, comprising turbine blades (2) with platforms (4), gaps be- tween the platforms (4) of adjacent turbine blades (2) and seals (10), each seal (10) covering the gap between the plat¬ forms (4) of two adjacent turbine blades (2) wherein the platforms are provided with slots in circumferential sides facing adjacent turbine blades (2), the turbine blades (2) comprising root cavities (6), wherein the seal (10) covers at least the whole length of the root cavities (6) of two adja¬ cent turbine blades (2), the seal is formed from a strip (10) and the seal (10) is placed in two opposed slots (8) formed in each of the platforms (4) of two adjacent turbine blades (2) and open towards their downstream ends.
2. A turbine blade assembly according to claim 1 or claim 2, characterised in that the seal (10) is made of a flexible, resilient material.
3. A turbine blade assembly according to any of the claims 1 to 3, characterised in that the seal (10) is locked in the blades (2) by locking plates which are assem¬ bled at the downstream end of the turbine disc (12) .
4. A gas turbine with a turbine blade assembly according to any of the previous claims .
5. Method for assembling a turbine blade assembly, in par- ticular for a gas turbine, wherein turbine blades (2) are as¬ sembled to a turbine disc (12) and seals (10) are assembled to platforms (4) of turbine blades (2) to cover gaps between the platforms (4) of adjacent turbine blades (2) , charac¬ terised in that all the turbine blades (2) are fit- ted to the turbine disc (12) before the seals are fitted be¬ tween the platforms (4) of adjacent turbine blades (2) .
6. Method for assembling turbine blades (2) according to claim 5, characterised in that the seals (10) are fitted from the downstream bladed disc face.
7. Method for assembling turbine blades (2) according to claim 6, characterised in that the seals (10) are inserted into and guided by opposing slots (8) in adja¬ cent platforms (4) by continuous motion.
PCT/EP2007/059084 2006-10-17 2007-08-31 Turbine blade assembly WO2008046684A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP07803092A EP2054588B1 (en) 2006-10-17 2007-08-31 Turbine blade assembly
US12/311,837 US8545181B2 (en) 2006-10-17 2007-08-31 Turbine blade assembly
CN2007800387455A CN101529054B (en) 2006-10-17 2007-08-31 Turbine blade assembly
ES07803092T ES2391419T3 (en) 2006-10-17 2007-08-31 Turbine blade set

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP06021770A EP1914386A1 (en) 2006-10-17 2006-10-17 Turbine blade assembly
EP06021770.0 2006-10-17

Publications (1)

Publication Number Publication Date
WO2008046684A1 true WO2008046684A1 (en) 2008-04-24

Family

ID=37905630

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2007/059084 WO2008046684A1 (en) 2006-10-17 2007-08-31 Turbine blade assembly

Country Status (6)

Country Link
US (1) US8545181B2 (en)
EP (2) EP1914386A1 (en)
CN (1) CN101529054B (en)
ES (1) ES2391419T3 (en)
RU (1) RU2415272C2 (en)
WO (1) WO2008046684A1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102245860A (en) * 2008-12-12 2011-11-16 斯奈克玛 Seal for a platform in the rotor of a turbine engine
EP2551464A1 (en) 2011-07-25 2013-01-30 Siemens Aktiengesellschaft Airfoil arrangement comprising a sealing element made of metal foam
EP3447248A1 (en) 2017-08-21 2019-02-27 Siemens Aktiengesellschaft Turbine blade assembly comprising a sealing element made of adhesive material
US10323531B2 (en) 2013-12-09 2019-06-18 Siemens Aktiengesellschaft Airfoil device for a gas turbine and corresponding arrangement
US20200347738A1 (en) * 2019-05-01 2020-11-05 United Technologies Corporation Seal for a gas turbine engine

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8820754B2 (en) 2010-06-11 2014-09-02 Siemens Energy, Inc. Turbine blade seal assembly
US8550785B2 (en) 2010-06-11 2013-10-08 Siemens Energy, Inc. Wire seal for metering of turbine blade cooling fluids
RU2557826C2 (en) * 2010-12-09 2015-07-27 Альстом Текнолоджи Лтд Gas turbine with axial hot air flow, and axial compressor
GB2486488A (en) 2010-12-17 2012-06-20 Ge Aviat Systems Ltd Testing a transient voltage protection device
US9017015B2 (en) * 2011-10-27 2015-04-28 General Electric Company Turbomachine including an inner-to-outer turbine casing seal assembly and method
US9039382B2 (en) * 2011-11-29 2015-05-26 General Electric Company Blade skirt
EP2762679A1 (en) * 2013-02-01 2014-08-06 Siemens Aktiengesellschaft Gas Turbine Rotor Blade and Gas Turbine Rotor
EP2843197B1 (en) 2013-08-29 2019-09-04 Ansaldo Energia Switzerland AG Blade for a rotary flow machine, the blade having specific retaining means for a radial strip seal
EP3292277A1 (en) * 2015-05-07 2018-03-14 Siemens Aktiengesellschaft Turbine airfoil with internal cooling channels
US9845690B1 (en) 2016-06-03 2017-12-19 General Electric Company System and method for sealing flow path components with front-loaded seal
CN106593952B (en) * 2017-01-12 2022-08-26 珠海格力电器股份有限公司 Axial flow fan blade and fan and air conditioner outdoor unit with same
EP3438410B1 (en) 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine
US10655489B2 (en) 2018-01-04 2020-05-19 General Electric Company Systems and methods for assembling flow path components
US11248705B2 (en) 2018-06-19 2022-02-15 General Electric Company Curved seal with relief cuts for adjacent gas turbine components
US11047248B2 (en) 2018-06-19 2021-06-29 General Electric Company Curved seal for adjacent gas turbine components
US11231175B2 (en) 2018-06-19 2022-01-25 General Electric Company Integrated combustor nozzles with continuously curved liner segments

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH525419A (en) 1970-12-18 1972-07-15 Bbc Sulzer Turbomaschinen Sealing device for turbo machines
GB1580884A (en) 1977-08-03 1980-12-10 Rolls Royce Sealing means
US4265594A (en) 1978-03-02 1981-05-05 Bbc Brown Boveri & Company Limited Turbine blade having heat localization segments
GB2182399A (en) 1985-10-30 1987-05-13 Rolls Royce Sealing means between two members
GB2280935A (en) 1993-06-12 1995-02-15 Rolls Royce Plc Cooled sealing strip for nozzle guide vane segments
GB2303888A (en) 1995-08-02 1997-03-05 Rolls Royce Plc Platform seal
JPH10184310A (en) 1996-12-24 1998-07-14 Hitachi Ltd Gas turbine stationary blade
WO2000057031A1 (en) 1999-03-19 2000-09-28 Siemens Aktiengesellschaft Gas turbine rotor with internally-cooled gas turbine blade
WO2004074640A1 (en) 2003-02-19 2004-09-02 Alstom Technology Ltd Sealing arrangement, particularly for the blade segments of gas turbines
GB2400144A (en) 2003-03-19 2004-10-06 Alstom Technology Ltd Sealing between turbine blade platforms
US20050186074A1 (en) 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3295825A (en) 1965-03-10 1967-01-03 Gen Motors Corp Multi-stage turbine rotor
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5531457A (en) 1994-12-07 1996-07-02 Pratt & Whitney Canada, Inc. Gas turbine engine feather seal arrangement
DE102004016174A1 (en) 2004-03-30 2005-10-20 Alstom Technology Ltd Baden Diaphragm gland for sealing a gap between first and second adjacent components in dynamical-type compressors/turbines has a sealing surface with a curved line
DE102004023130A1 (en) 2004-05-03 2005-12-01 Rolls-Royce Deutschland Ltd & Co Kg Sealing and damping system for turbine blades
US8011892B2 (en) * 2007-06-28 2011-09-06 United Technologies Corporation Turbine blade nested seal and damper assembly

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH525419A (en) 1970-12-18 1972-07-15 Bbc Sulzer Turbomaschinen Sealing device for turbo machines
GB1580884A (en) 1977-08-03 1980-12-10 Rolls Royce Sealing means
US4265594A (en) 1978-03-02 1981-05-05 Bbc Brown Boveri & Company Limited Turbine blade having heat localization segments
GB2182399A (en) 1985-10-30 1987-05-13 Rolls Royce Sealing means between two members
GB2280935A (en) 1993-06-12 1995-02-15 Rolls Royce Plc Cooled sealing strip for nozzle guide vane segments
GB2303888A (en) 1995-08-02 1997-03-05 Rolls Royce Plc Platform seal
JPH10184310A (en) 1996-12-24 1998-07-14 Hitachi Ltd Gas turbine stationary blade
WO2000057031A1 (en) 1999-03-19 2000-09-28 Siemens Aktiengesellschaft Gas turbine rotor with internally-cooled gas turbine blade
WO2004074640A1 (en) 2003-02-19 2004-09-02 Alstom Technology Ltd Sealing arrangement, particularly for the blade segments of gas turbines
GB2400144A (en) 2003-03-19 2004-10-06 Alstom Technology Ltd Sealing between turbine blade platforms
US20050186074A1 (en) 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102245860A (en) * 2008-12-12 2011-11-16 斯奈克玛 Seal for a platform in the rotor of a turbine engine
EP2551464A1 (en) 2011-07-25 2013-01-30 Siemens Aktiengesellschaft Airfoil arrangement comprising a sealing element made of metal foam
WO2013013975A1 (en) 2011-07-25 2013-01-31 Siemens Aktiengesellschaft Airfoil arrangement comprising a sealing element made of metal foam
US10323531B2 (en) 2013-12-09 2019-06-18 Siemens Aktiengesellschaft Airfoil device for a gas turbine and corresponding arrangement
EP3447248A1 (en) 2017-08-21 2019-02-27 Siemens Aktiengesellschaft Turbine blade assembly comprising a sealing element made of adhesive material
US20200347738A1 (en) * 2019-05-01 2020-11-05 United Technologies Corporation Seal for a gas turbine engine
US11111802B2 (en) * 2019-05-01 2021-09-07 Raytheon Technologies Corporation Seal for a gas turbine engine

Also Published As

Publication number Publication date
US20100178173A1 (en) 2010-07-15
EP1914386A1 (en) 2008-04-23
ES2391419T3 (en) 2012-11-26
CN101529054B (en) 2012-06-20
EP2054588A1 (en) 2009-05-06
CN101529054A (en) 2009-09-09
US8545181B2 (en) 2013-10-01
EP2054588B1 (en) 2012-08-01
RU2009118436A (en) 2010-11-27
RU2415272C2 (en) 2011-03-27

Similar Documents

Publication Publication Date Title
EP2054588B1 (en) Turbine blade assembly
EP1959101B1 (en) Turbine rotor with cover plate
JP6279786B2 (en) Gas turbine rotor blade, gas turbine rotor, and method of assembling rotor assembly
EP2586975B1 (en) Turbine bucket with platform shaped for gas temperature control, corresponding turbine wheel and method of controlling purge air flow
EP2586995B1 (en) Turbine bucket angel wing features for forward cavity flow control and related method
US7967559B2 (en) Stator-rotor assembly having surface feature for enhanced containment of gas flow and related processes
EP2055898B1 (en) Gas turbine engine with circumferential array of airfoils with platform cooling
US9534500B2 (en) Seal arrangement for segmented gas turbine engine components
EP2586974B1 (en) Turbine bucket with platform leading edge scallop for performance and secondary flow, corresponding turbine wheel and method of controlling secondary purge air flow
US8573925B2 (en) Cooled component for a gas turbine engine
US8585354B1 (en) Turbine ring segment with riffle seal
EP3002410A1 (en) A bladed rotor arrangement with lock plates and seal plates
US20070148002A1 (en) Turbine blade retaining apparatus
EP2649279B1 (en) Fluid flow machine especially gas turbine penetrated axially by a hot gas stream
US20170175557A1 (en) Gas turbine sealing
EP2844843B1 (en) Sealing arrangement for a nozzle guide vane and gas turbine
EP3653844A1 (en) Strip seal, annular segment and method for a gas turbine
EP2184444B1 (en) Blade attachment apparatus for a turbine

Legal Events

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

Ref document number: 200780038745.5

Country of ref document: CN

121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 07803092

Country of ref document: EP

Kind code of ref document: A1

WWE Wipo information: entry into national phase

Ref document number: 2007803092

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 12311837

Country of ref document: US

NENP Non-entry into the national phase

Ref country code: DE

ENP Entry into the national phase

Ref document number: 2009118436

Country of ref document: RU

Kind code of ref document: A