GB2298246A - Turbine-blad-tip-sealing arrangement comprising a shroud band - Google Patents

Turbine-blad-tip-sealing arrangement comprising a shroud band Download PDF

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Publication number
GB2298246A
GB2298246A GB9503575A GB9503575A GB2298246A GB 2298246 A GB2298246 A GB 2298246A GB 9503575 A GB9503575 A GB 9503575A GB 9503575 A GB9503575 A GB 9503575A GB 2298246 A GB2298246 A GB 2298246A
Authority
GB
United Kingdom
Prior art keywords
shroud band
slot
air
turbine
sealing rib
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
GB9503575A
Other versions
GB2298246B (en
GB9503575D0 (en
Inventor
Neil Milner Evans
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
BMW Rolls Royce GmbH
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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Priority to GB9503575A priority Critical patent/GB2298246B/en
Publication of GB9503575D0 publication Critical patent/GB9503575D0/en
Priority to DE19601818A priority patent/DE19601818C2/en
Publication of GB2298246A publication Critical patent/GB2298246A/en
Application granted granted Critical
Publication of GB2298246B publication Critical patent/GB2298246B/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2240/81—Cooled platforms
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Description

1 2298246 A turbine-blade arrangement comprising a shroud band The
invention relates to a turbine blade arrangement comprising a shroud band with at least one circumferential sealing rib, as known for example from WO 94/11616. The aim, by means of one or more circumferential sealing ribs on the shroud band, is greatly to reduce losses through leakage via the gap between the shroud banl and the wall of the casing or duct through which flow takes place.
The aim of the present invention is to disclose steps for still further reducing these leakage losses. To this end, the sealing rib has a circumferential slot, and a stream of air is supplied to the base of the slot and flows out at the top edge of the sealing rib. Advantageous other features are disclosed in the sub-claims.
According to the invention, the leakage flow is reduced by an air stream which flows substantially transversely with respect to the leakage flow between the wall of the casing or duct and the top edge of the sealing rib (s) and which f lows out of the aforementioned top edge. As a result, turbulence occurs in the gap between the casing or duct wall and the top edge of the sealing rib (s), and this turbulence hinders the leakage flow. Optionally the flow of air supplied to the bottom region of the slot can be branched off from the leakage flow upstream of the sealing rib(s), or alternatively the air flowing into the slot can be obtained from a cooling-air duct provided in the turbine blade, or preferably in the shroud band, for supplying air to cool these components.
The invention will now be explained in detail with reference to a preferred embodiment shown in the accompanying drawings, in which:
Figure 1 is a part section through a shroud band segment associated with a turbine blade in accordance with the invention; Figure 2 is a view X of Figure 1; and Figure 3 is a section taken on the line A-A in Figure 1.
Reference 1 denotes a turbine blade, more especially that used in a highpressure turbine or an aircraft gas turbine. The turbine blade carries a shroud-band segment 2, hereinafter also called a shroud band 2, and cooperates in a known manner with the other shroud-band segments of the adjacent blades to form a circumferential shroud band. At the top, the shroud band 2 has three sealing ribs 3, 4, 5 disposed one behind the other in the axial direction of the turbine. The ribs 3, 4, 5 are adapted to seal the gap on the side of the diagrammatically-indicated casing or duct wall 6 and thereby greatly reduce the leakage air flow represented by arrows 7. The sealing effect is improved by an additional air flow 8 from the top edge 5a of the sealing rib 5 into the gap between the sealing rib 5 and the wall 6. violent turbulence consequently occurs in the gap between the leakage air flow 7 and the air flow 8, thus further throttling the leakage air flow 7.
To obtain a uniform distribution of the air flow 8 around the entire periphery of the rotating shroud band 2 or of the likewise rotating sealing rib 5, the sealing rib 5 has - 3 a likewise circumferential slot 9 through which the sealing air flow 8 is guided. Consequently the air flow 8 from the slot 9 enters the gap between the tunnel wall 6 and the top edge Sa of the sealing ribs.
The air flow 8 can be supplied from various sources. A f irst embodiment is shown in Figures 1 to 3, in which a number of branch ducts 10 from a cooling-air duct 11 in the shroud band 2 open into the bottom region 9a of the slot 9. The shroud band in Figures 1 to 3 is provided with a cooling-air duct 11 and an entire cooling-air duct system 12 which supplies the cooling-air duct 11 and, in turn, is connected to a coolingair duct system (not shown) inside the air-cooled turbine blade 1. The air flow 8 is thus supplied from the flow of cooling air guided through the turbine blade 1 and the shroud band or segment 2.
The detailed manufacturing process can be as follows: firstly, the slot 9 is formed in a sealing rib 5, which is made wider than a conventional sealing rib without a slot. Next, the branch ducts 10 are manufactured, e. g. by drilling or electro-erosion. Preferably the branch ducts 10 enter the slot 9 at an inclined angle, as shown especially in Figure 3. By this means, the air flow 8 exhausts in the peripheral direction, i.e. opposing the direction of the rotating shroud band 2, imposing additional torque to the rotating stage to that of the blades in the neighbourhood of the top edge 5a of the sealing rib 5 so that the desired turbulence of the two air flows 7 and 8 is reliably produced in the gap between the top edge 5a and the tunnel wall 6. Finally, in the turbine-blade 4 arrangement shown in Figures 1 to 3, the cooling-air supply duct 13, which for manufacturing reasons extends through the cooling-air duct 11, is closed by welding on the trailing edge 2a of the shroud band 2 so that substantially the entire cooling-air flow is available as the air flow 8.
In the previously-explained embodiment, the sealing rib 5 formed with the circumferential slot 9 is on the trailing-edge side 2a of the cover shroud 2, since the leakage air flow 7 here has already been throttled by the upstream sealing ribs 3 and 4. The additional sealing effect is thus intensified by the air 8 flowing transversely into the gap.
The disclosed steps are a simple method of increasing the sealing effect in the gapregion between a turbine-blade shroud band 2 and the adjacent casing or duct wall 6. The additional expense is kept relatively low, and of course a number of details, particularly constructional, can deviate from the embodiment shown without departing from the scope of the claims.
4

Claims (3)

C L A I M S
1. A turbine blade arrangement comprising a shroud band (2) with at least one circumferential sealing rib (5), characterised in that the sealing rib (5) has a circumferential slot (9), whereby a stream of air (8) supplied to the base (9a) of the slot (9) is able to flow. out at the top edge (5a) of the sealing rib (5).
2. A turbine blade arrangement according to claim 1, having at least one cooling-air duct (11) in the shroud band (2), characterised in that branch ducts (10) extend from the cooling-air duct (11) and open into the bottom region (9a) of the slot (9).
3. A turbine blade arrangement according to claim 1 or claim 2, characterised in that the branch ducts (10) open into the slot (9) at an inclined angle.
A turbine blade arrangement according to any one of the preceding claims, characterised in that a number of circumferential sealing ribs (3, 4, 5) are disposed on the shroud band (2), and the sealing rib (5) formed with the circumferential slot (9) is situated on the trailing edge (2a) of the shroud band (2).
GB9503575A 1995-02-23 1995-02-23 A turbine-blade arrangement comprising a shroud band Expired - Fee Related GB2298246B (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB9503575A GB2298246B (en) 1995-02-23 1995-02-23 A turbine-blade arrangement comprising a shroud band
DE19601818A DE19601818C2 (en) 1995-02-23 1996-01-19 Turbine blade arrangement with a shroud

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9503575A GB2298246B (en) 1995-02-23 1995-02-23 A turbine-blade arrangement comprising a shroud band

Publications (3)

Publication Number Publication Date
GB9503575D0 GB9503575D0 (en) 1995-04-12
GB2298246A true GB2298246A (en) 1996-08-28
GB2298246B GB2298246B (en) 1998-10-28

Family

ID=10770086

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9503575A Expired - Fee Related GB2298246B (en) 1995-02-23 1995-02-23 A turbine-blade arrangement comprising a shroud band

Country Status (2)

Country Link
DE (1) DE19601818C2 (en)
GB (1) GB2298246B (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2322167A (en) * 1996-12-17 1998-08-19 Gen Electric Turbine blade with squealer tip cooling
GB2413160A (en) * 2004-04-17 2005-10-19 Rolls Royce Plc A rotor blade tip cooling arrangement
GB2434842A (en) * 2006-02-02 2007-08-08 Rolls Royce Plc Cooling arrangement for a turbine blade shroud
GB2451568A (en) * 2007-07-31 2009-02-04 Gen Electric Seal tooth arrangement for gas turbine engine rotor blade tip shroud
CH699593A1 (en) * 2008-09-25 2010-03-31 Alstom Technology Ltd Blade for a gas turbine.
EP1793086A3 (en) * 2005-12-03 2012-04-25 Rolls-Royce plc Turbine blade
AU2010230482B2 (en) * 2009-03-30 2014-12-04 Ansaldo Energia Ip Uk Limited Blade for a gas turbine
RU2541078C2 (en) * 2010-05-05 2015-02-10 Альстом Текнолоджи Лтд Turbine blade and procedure for its manufacture
WO2017023258A1 (en) * 2015-07-31 2017-02-09 General Electric Company Cooling arrangements in turbine blades
EP3168423A1 (en) * 2015-11-16 2017-05-17 General Electric Company Rotor blade with tip shroud cooling passages and method of making same
JP2017115716A (en) * 2015-12-24 2017-06-29 三菱日立パワーシステムズ株式会社 Seal device
US9777577B2 (en) 2012-02-17 2017-10-03 Ansaldo Energia Ip Uk Limited Component for a thermal machine, in particular a gas turbine
EP3412869A1 (en) * 2017-06-07 2018-12-12 General Electric Company Turbomachine rotor blade

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59912323D1 (en) * 1998-12-24 2005-09-01 Alstom Technology Ltd Baden Turbine blade with actively cooled Deckbandelememt
DE19904229A1 (en) * 1999-02-03 2000-08-10 Asea Brown Boveri Cooled turbine blade has shroud formed by sealing rib with integrated cooling channels connected to coolant channel in blade
EP1041247B1 (en) * 1999-04-01 2012-08-01 General Electric Company Gas turbine airfoil comprising an open cooling circuit
DE10336863A1 (en) * 2002-09-17 2004-03-25 Alstom (Switzerland) Ltd. Thermal turbo-machine e.g. gas turbine, has at least two adjacent turbine vanes, and continuous cover band that extends in rear part of vane to smallest cross-section region of maximum plus/minus 3 per cent of chord length
US6887033B1 (en) * 2003-11-10 2005-05-03 General Electric Company Cooling system for nozzle segment platform edges
DE102007037855A1 (en) * 2007-08-10 2009-02-12 Rolls-Royce Deutschland Ltd & Co Kg Vane cover tape with blocking jet generation
US20140023497A1 (en) * 2012-07-19 2014-01-23 General Electric Company Cooled turbine blade tip shroud with film/purge holes

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB855058A (en) * 1957-02-22 1960-11-30 Rolls Royce Improvements in or relating to bladed rotor or stator constructions for axial-flow fluid machines for example for compressors or turbines of gas-turbine engines
GB895615A (en) * 1960-02-05 1962-05-02 Rolls Royce A method and apparatus for forming non-circular holes
GB1437617A (en) * 1972-09-01 1976-06-03 Gen Electric Gas turbine
GB2075129A (en) * 1980-05-01 1981-11-11 Gen Electric Tip cap for a rotor blade and method of replacement
GB2228540A (en) * 1988-12-07 1990-08-29 Rolls Royce Plc Cooling of turbine blades
WO1994011616A1 (en) * 1992-11-19 1994-05-26 Bmw Rolls-Royce Gmbh Cooling of the shroud of a turbine blade

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB855058A (en) * 1957-02-22 1960-11-30 Rolls Royce Improvements in or relating to bladed rotor or stator constructions for axial-flow fluid machines for example for compressors or turbines of gas-turbine engines
GB895615A (en) * 1960-02-05 1962-05-02 Rolls Royce A method and apparatus for forming non-circular holes
GB1437617A (en) * 1972-09-01 1976-06-03 Gen Electric Gas turbine
GB2075129A (en) * 1980-05-01 1981-11-11 Gen Electric Tip cap for a rotor blade and method of replacement
GB2228540A (en) * 1988-12-07 1990-08-29 Rolls Royce Plc Cooling of turbine blades
WO1994011616A1 (en) * 1992-11-19 1994-05-26 Bmw Rolls-Royce Gmbh Cooling of the shroud of a turbine blade

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2322167A (en) * 1996-12-17 1998-08-19 Gen Electric Turbine blade with squealer tip cooling
GB2322167B (en) * 1996-12-17 2001-02-07 Gen Electric Turbine blade
GB2413160A (en) * 2004-04-17 2005-10-19 Rolls Royce Plc A rotor blade tip cooling arrangement
GB2413160B (en) * 2004-04-17 2006-08-09 Rolls Royce Plc Turbine rotor blades
US7632062B2 (en) 2004-04-17 2009-12-15 Rolls-Royce Plc Turbine rotor blades
EP1793086A3 (en) * 2005-12-03 2012-04-25 Rolls-Royce plc Turbine blade
GB2434842A (en) * 2006-02-02 2007-08-08 Rolls Royce Plc Cooling arrangement for a turbine blade shroud
GB2451568A (en) * 2007-07-31 2009-02-04 Gen Electric Seal tooth arrangement for gas turbine engine rotor blade tip shroud
GB2451568B (en) * 2007-07-31 2012-06-27 Gen Electric Rotor blade
CH699593A1 (en) * 2008-09-25 2010-03-31 Alstom Technology Ltd Blade for a gas turbine.
WO2010034669A1 (en) * 2008-09-25 2010-04-01 Alstom Technology Ltd. Vane for a gas turbine
US8764395B2 (en) 2008-09-25 2014-07-01 Alstom Technology Ltd. Blade for a gas turbine
AU2010230482B2 (en) * 2009-03-30 2014-12-04 Ansaldo Energia Ip Uk Limited Blade for a gas turbine
RU2543641C2 (en) * 2009-03-30 2015-03-10 Альстом Текнолоджи Лтд. Gas turbine blade
US9464529B2 (en) 2009-03-30 2016-10-11 General Electric Technology Gmbh Blade for a gas turbine
RU2541078C2 (en) * 2010-05-05 2015-02-10 Альстом Текнолоджи Лтд Turbine blade and procedure for its manufacture
US9777577B2 (en) 2012-02-17 2017-10-03 Ansaldo Energia Ip Uk Limited Component for a thermal machine, in particular a gas turbine
WO2017023258A1 (en) * 2015-07-31 2017-02-09 General Electric Company Cooling arrangements in turbine blades
US10605099B2 (en) 2015-07-31 2020-03-31 General Electric Company Cooling arrangements in turbine blades
EP3168423A1 (en) * 2015-11-16 2017-05-17 General Electric Company Rotor blade with tip shroud cooling passages and method of making same
US10202852B2 (en) 2015-11-16 2019-02-12 General Electric Company Rotor blade with tip shroud cooling passages and method of making same
JP2017115716A (en) * 2015-12-24 2017-06-29 三菱日立パワーシステムズ株式会社 Seal device
EP3412869A1 (en) * 2017-06-07 2018-12-12 General Electric Company Turbomachine rotor blade
US10502069B2 (en) 2017-06-07 2019-12-10 General Electric Company Turbomachine rotor blade

Also Published As

Publication number Publication date
DE19601818C2 (en) 2003-06-18
GB2298246B (en) 1998-10-28
GB9503575D0 (en) 1995-04-12
DE19601818A1 (en) 1996-08-29

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 20100223