EP1623097A1 - Steam/gas turbine pressure stage with universal shroud - Google Patents

Steam/gas turbine pressure stage with universal shroud

Info

Publication number
EP1623097A1
EP1623097A1 EP03726350A EP03726350A EP1623097A1 EP 1623097 A1 EP1623097 A1 EP 1623097A1 EP 03726350 A EP03726350 A EP 03726350A EP 03726350 A EP03726350 A EP 03726350A EP 1623097 A1 EP1623097 A1 EP 1623097A1
Authority
EP
European Patent Office
Prior art keywords
shroud
steam
gas
ridge
turbine
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.)
Withdrawn
Application number
EP03726350A
Other languages
German (de)
French (fr)
Other versions
EP1623097A4 (en
Inventor
Oleg Naljotov
Vladlen Zitin
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of EP1623097A1 publication Critical patent/EP1623097A1/en
Publication of EP1623097A4 publication Critical patent/EP1623097A4/en
Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/007—Preventing corrosion
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/602—Drainage
    • 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
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • 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

Definitions

  • the invention relates to the field of turbine and air compressor construction, more precisely to steam turbines as well as gas turbines and air compressor pressure stages, incorporating sealed shroud on turbine rotor blades, said seals located on shroud or incorporated in turbine stator.
  • the invention can be used in the development of steam turbines at turbine manufacturing plants, as well as in enhancement of steam and gas turbines at heat power stations and that of aircraft engines with gas turbines and compressors.
  • Shroud seals of a turbine stage consist as a rule of two ridges, with the first ridge 4 following the direction of steam flow located in the seal and the second ridge 5, both of which form a shroud chamber 11, located over the shroud, comprising radial clearances hi and h2, determining the flow rate of steam, coming through seal.
  • Clearances hi and h2 are set equal in absolute value for each stage or stage group, said value depending on the conditions of thermal expansion of turbine parts, as well as on the conditions of turbo-unit threshold power, i.e. power, producing low frequency vibration.
  • Rotor blade shroud 8 with layouts represented on Fig.3 and Fig.4 are in the form of a strip with openings 15 for rotor blade pins 9, which are unriveted after their mounting on rotor blades, forming a pack of six or more blades. Parts 13 of these shroud, covering single flow channel do not have any openings.
  • the purpose of the invention is the improvement of steam and gas turbines operation reliability, the increase of actual efficiency factor and power as compared to the existing parameters.
  • the abovementioned purpose is achieved by way of making of clearances hi and h2 in the ridges of shroud seals in such a manner, that the radial seal h2 on the second ridge 5 is smaller than the radial clearance hi on the first ridge 4, which permits to regulate the flow rate of steam, coming through shroud chamber 11 within specified limits.
  • a system of discharge openings 12 is implemented in rotor blade shroud parts 13, covering single inter-blade channel, by way of drilling of the shroud Fig. 5 and Fig.6.
  • the openings are located evenly along the surface of parts 13 and 14 of the shroud 8, following the direction of steam flow 18 Fig.4 in inter-blade channel 14. Said openings may be organized in staggered order 16, depending on the properties of deposits and their volume, as well as on seals design.
  • the ratio between the number of openings n and their diameter d is the following:
  • Sk is the square of the shroud's part, covering each single inter-blade channel in rotor wheel. Due to openings 12 in the shroud 8 of rotor blades 7 there occurs in the course of turbine operation a steam overflow from the chamber 11 located above the shroud and enclosure 17, also above the shroud Fig. 5 to the part of flow channel, located under the shroud, which leads to the creation of an obstacle effect, preventing the formation of metal and salt oxides on the inner surface of the shroud.
  • the invention can be used for the following purposes: a) as means, preventing the formation of metal and salt oxides on the inner surfaces of rotor blade shrouds; b) as means for the enhancement of turbo-unit vibration state c) with the purpose of prolongation of period between repairs owing to p.p. a) and b) and that of turbine service life.
  • the invention refers to the manufacture and operation of steam and gas turbines, compressed air plants and gas force pumps.
  • Fig.l - a longitudinal section of turbine pressure stage with shroud seals in the nozzle block shield.
  • Fig.2 - a longitudinal section of turbine pressure stage with shroud seals, located in rotor blade shrouds.
  • Fig.3 - a shroud section of Fig.1;
  • Fig.4 - a shroud section of Fig.2;
  • Fig.5 - a detail of Fig.2 with section along D-D
  • Fig.6 - a detail of F ⁇ g.l with section along C-C
  • a steam (gas) turbine (compressor) pressure stage Fig.l and Fig.2. comprising a nozzle (directional) block 1 with nozzle (directional) blades 2 and a shield 3, seal shroud ridges 4 and 5 or ridges 4 and 5, located on the shroud 8 Fig.2 and rotor wheel with shroud 8, located on rotor blades 7 differs in the respect, that with the purpose of increasing the efficiency factor and operational reliability of turbine, radial clearance h2 of the second ridge 5 of shroud seal, located along the steam/gas flow is made less than radial clearance hi of the ridge 4 of the shroud seal and in parts 13,14,15 of the shroud 8, closing the single inter-blade channel there is a system of radial discharge openings 12 Fig.3., Fig.4, Fig.5 and Fig.6, distributed evenly in relation to the surfaces of parts 13, 14, 16 of shroud 8.
  • Said radial discharge openings can also be organized in staggered order 16, as well as along medium steam flow line 14 and 18, or in symmetrical position to steam flow line 18 Fig.4 in the inter-blade channel, for steam (gas) overflow from the enclosure 17 above the shroud Fig.5 and chamber 11 above the shroud to the flow channel and the discharge of above shroud pressure, said pressure being the source of air dynamic above shroud and ridge "Thomas forces", which induce unstable operation of turbine rotor and its supports, whereas steam (gas), entering through the discharge openings 12 in shroud 8 to the above shroud enclosure of the flow channel prevents the formation of metal and salt oxides 10 on the inner surface of shroud 8 with the diameter d_of the openings 12 and their number n on each surface Sk of each flow channel of shroud parts 13,14, 16, covering the single inter-blade channel stand in the following ratio:

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

Imperfect design of shroudS (8) or identical parts of the blades (7) of steam/gas turbines, including the adjoining seals, leads to a decrease in reliability and efficiency. These drawbacks are eliminated by the use of drilled radial holes (12) in the shroud of the blades (7). The transfer of steam through the shroud holes (12) results in the relief of the pressures gradient on the surface of the shroud (8) and prevents the formation of metal oxide, salt and other deposits on the inner surfaces of the shroud (8). The quantity and diameter of the holes (12), as well as their corresponding disposition and the values of radial clearances in shroud crowning seals (4, 5) regulate their efficiency.

Description

Title of invention
'Steam/gas turbine pressure stage with universal shroud':
Background and prior art
The invention relates to the field of turbine and air compressor construction, more precisely to steam turbines as well as gas turbines and air compressor pressure stages, incorporating sealed shroud on turbine rotor blades, said seals located on shroud or incorporated in turbine stator.
The invention can be used in the development of steam turbines at turbine manufacturing plants, as well as in enhancement of steam and gas turbines at heat power stations and that of aircraft engines with gas turbines and compressors.
Known are steam turbine pressure stages designs (Fig.l and Fig.2) with nozzle (directional) block 1 with nozzle (directional) blades 2 and shield 3, a rotor wheel, consisting of disc 6, rotor blades 1, a shroud 8 and shroud seals 4 and 5, incorporated in the shield 3 of the nozzle block
Fig.l or Fig.2 or located on the shroud of rotor blades Fig.2.
Shroud seals of a turbine stage consist as a rule of two ridges, with the first ridge 4 following the direction of steam flow located in the seal and the second ridge 5, both of which form a shroud chamber 11, located over the shroud, comprising radial clearances hi and h2, determining the flow rate of steam, coming through seal.
Clearances hi and h2 are set equal in absolute value for each stage or stage group, said value depending on the conditions of thermal expansion of turbine parts, as well as on the conditions of turbo-unit threshold power, i.e. power, producing low frequency vibration.
Rotor blade shroud 8, with layouts represented on Fig.3 and Fig.4 are in the form of a strip with openings 15 for rotor blade pins 9, which are unriveted after their mounting on rotor blades, forming a pack of six or more blades. Parts 13 of these shroud, covering single flow channel do not have any openings.
Steam or gas turbine stages described Fig.l and Fig.2 possesses the following significant flaws, revealed in the course of turbine operation: a) Due to the uneven distribution of clearances in shroud seals around the stage, there emerge air dynamic shroud and ridge Thomas forces, inducing unstable operation of turbine rotor and its supports; b) Inner surface 8 of rotor blade shroud is subject to the formation of metal and salt oxides 10, the presence of which closes a portion of rotor blade open flow area, which leads to the decrease of rated efficiency factor with subsequent reduction of turbine power. c) Excessive fuel combustion, owing to p. b) with varying comparative turbine loads leads to the extra consumption of fuel resources.
The purpose of the invention is the improvement of steam and gas turbines operation reliability, the increase of actual efficiency factor and power as compared to the existing parameters. The abovementioned purpose is achieved by way of making of clearances hi and h2 in the ridges of shroud seals in such a manner, that the radial seal h2 on the second ridge 5 is smaller than the radial clearance hi on the first ridge 4, which permits to regulate the flow rate of steam, coming through shroud chamber 11 within specified limits. A system of discharge openings 12 is implemented in rotor blade shroud parts 13, covering single inter-blade channel, by way of drilling of the shroud Fig. 5 and Fig.6. The openings are located evenly along the surface of parts 13 and 14 of the shroud 8, following the direction of steam flow 18 Fig.4 in inter-blade channel 14. Said openings may be organized in staggered order 16, depending on the properties of deposits and their volume, as well as on seals design. The ratio between the number of openings n and their diameter d is the following:
(0,02 ÷ 0,50) -Sk d= 2 n -π
Where Sk is the square of the shroud's part, covering each single inter-blade channel in rotor wheel. Due to openings 12 in the shroud 8 of rotor blades 7 there occurs in the course of turbine operation a steam overflow from the chamber 11 located above the shroud and enclosure 17, also above the shroud Fig. 5 to the part of flow channel, located under the shroud, which leads to the creation of an obstacle effect, preventing the formation of metal and salt oxides on the inner surface of the shroud.
The discharge of pressure from the chamber 11 located over the shroud and enclosure 17 over the shrouds is implemented by similar process of steam overflow, which process excludes the onset of air dynamic above shroud and ridge Thomas forces, inducing unstable operation of turbine rotor and its supports. This, in turn, facilitates the reduction of radial clearance h2 on the second ridge 5, controlling the turbo-unit threshold power, which results in additional increase of the efficiency factor owing to the reduction of steam overflow over the seal. Thus, the invention can be used for the following purposes: a) as means, preventing the formation of metal and salt oxides on the inner surfaces of rotor blade shrouds; b) as means for the enhancement of turbo-unit vibration state c) with the purpose of prolongation of period between repairs owing to p.p. a) and b) and that of turbine service life.
Field of the invention
The invention refers to the manufacture and operation of steam and gas turbines, compressed air plants and gas force pumps.
Imperfect design of belt shrouds or identical parts of the blades of such machines, including the adjoining seals, leads to the decrease in reliability and efficiency.
1. Uneven distribution of radial clearances along the shrouds' circumference induces the effect of air-dynamic Thomas forces, decreasing vibration behavior.
2. The inner surface of shrouds is subjected to formation of metal oxide and salt deposits. These drawbacks are eliminated by way of drilling of radial holes in the shrouds of the blades. The transfer of steam through the shroud holes results in the relief of the pressures gradient on the surface of the shroud and prevents the formation of metal oxide, salt and other deposits on the inner surfaces of the shrouds.
The quantity and diameter of the holes, as well as their corresponding disposition and the values of radial clearances in shroud crowning seals regulate their efficiency.
Brief description of the figures of the drawings
A list of figures:
Fig.l - a longitudinal section of turbine pressure stage with shroud seals in the nozzle block shield.
Fig.2 - a longitudinal section of turbine pressure stage with shroud seals, located in rotor blade shrouds.
Fig.3 - a shroud section of Fig.1;
Fig.4 - a shroud section of Fig.2;
Fig.5 - a detail of Fig.2 with section along D-D
Fig.6 - a detail of F^g.l with section along C-C
Summary of the invention
A steam (gas) turbine (compressor) pressure stage Fig.l and Fig.2. comprising a nozzle (directional) block 1 with nozzle (directional) blades 2 and a shield 3, seal shroud ridges 4 and 5 or ridges 4 and 5, located on the shroud 8 Fig.2 and rotor wheel with shroud 8, located on rotor blades 7 differs in the respect, that with the purpose of increasing the efficiency factor and operational reliability of turbine, radial clearance h2 of the second ridge 5 of shroud seal, located along the steam/gas flow is made less than radial clearance hi of the ridge 4 of the shroud seal and in parts 13,14,15 of the shroud 8, closing the single inter-blade channel there is a system of radial discharge openings 12 Fig.3., Fig.4, Fig.5 and Fig.6, distributed evenly in relation to the surfaces of parts 13, 14, 16 of shroud 8. Said radial discharge openings can also be organized in staggered order 16, as well as along medium steam flow line 14 and 18, or in symmetrical position to steam flow line 18 Fig.4 in the inter-blade channel, for steam (gas) overflow from the enclosure 17 above the shroud Fig.5 and chamber 11 above the shroud to the flow channel and the discharge of above shroud pressure, said pressure being the source of air dynamic above shroud and ridge "Thomas forces", which induce unstable operation of turbine rotor and its supports, whereas steam (gas), entering through the discharge openings 12 in shroud 8 to the above shroud enclosure of the flow channel prevents the formation of metal and salt oxides 10 on the inner surface of shroud 8 with the diameter d_of the openings 12 and their number n on each surface Sk of each flow channel of shroud parts 13,14, 16, covering the single inter-blade channel stand in the following ratio:
(0,02 ÷ 0,50) -Sk d= 2 n -π

Claims

Claim of the inventionWe are Oleg Nalotov and Vladlen Zitin, have invented a new design for a Steam (gas) turbine (compressor) as set forth in the following specification.
1. Fig 1 - 2. Radial clearance h2 of the second ridge 5 of shroud seal, located along the steam/gas flow is made less than radial clearance hi of the ridge 4 of the shroud seal.
2. Fig 3 - 4 - 5 - 6. In parts 13, 14, 15 of the shroud 8, closing the single inter-blade channel there is a system of radial discharge openings 12, distributed evenly in relation to the surfaces of parfe 13, 14, 16 of shroud 8. Said radial discharge openings can also be organized in staggered order 16, as well as along medium steam flow line 14 and 18, or in symmetrical position to steam flow line 18 Fig.4 in the inter-blade channel, for steam (gas) overflow from the enclosure 17 above the shroud Fig.5 and chamber 11 above the shroud to the flow channel and the discharge of above shroud pressure, said pressure being the source of air dynamic above shroud and ridge "Thomas forces", which induce unstable operation of turbine rotor and its supports, whereas steam (gas), entering through the discharge openings 12 in shroud 8 to the above shroud enclosure of the flow channel prevents the formation of metal and salt oxides 10 on the inner surface of shroud 8 with the diameter d of the openings 12 and their number n on each surface Sk of each flow channel of shroud parts 13,14, 16, covering the single inter-blade channel stand in the following ratio:
d= 2 (0,02 ÷ 0,50) -Sk n -π
EP03726350A 2003-04-18 2003-04-18 Steam/gas turbine pressure stage with universal shroud Withdrawn EP1623097A4 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2003/012102 WO2004099572A1 (en) 2003-04-18 2003-04-18 Steam/gas turbine pressure stage with universal shroud

Publications (2)

Publication Number Publication Date
EP1623097A1 true EP1623097A1 (en) 2006-02-08
EP1623097A4 EP1623097A4 (en) 2012-06-27

Family

ID=33434336

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03726350A Withdrawn EP1623097A4 (en) 2003-04-18 2003-04-18 Steam/gas turbine pressure stage with universal shroud

Country Status (9)

Country Link
EP (1) EP1623097A4 (en)
JP (1) JP4195882B2 (en)
CN (1) CN100386502C (en)
AU (1) AU2003228590B2 (en)
BR (1) BR0318261A (en)
CA (1) CA2562712C (en)
EA (1) EA008156B1 (en)
UA (1) UA81314C2 (en)
WO (1) WO2004099572A1 (en)

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE893649C (en) * 1940-05-04 1953-10-19 Siemens Ag Installation on steam or gas turbine blades
FR2166494A5 (en) * 1971-12-27 1973-08-17 Onera (Off Nat Aerospatiale)
SU663861A1 (en) * 1977-08-23 1979-05-25 Ленинградский Ордена Ленина Политехнический Институт Им.М.И.Калинина Axial turbine runner
JPS55146201A (en) * 1979-05-04 1980-11-14 Hitachi Ltd Moving blade for turbine
US4534701A (en) * 1982-06-29 1985-08-13 Gerhard Wisser Rotor or guide wheel of a turbine engine with shroud ring
DE3505491A1 (en) * 1985-02-16 1986-08-21 MTU Motoren- und Turbinen-Union München GmbH, 8000 München GASKET FOR A FLUID MACHINE
DE4015206C1 (en) * 1990-05-11 1991-10-17 Mtu Muenchen Gmbh
FR2661944B1 (en) * 1990-05-14 1994-06-10 Alsthom Gec TURBOMACHINE FLOOR WITH REDUCED SECONDARY LOSSES.
FR2666846B1 (en) * 1990-09-13 1992-10-16 Alsthom Gec VANE GRILLE FOR TURBOMACHINE PROVIDED WITH SUCTION SLOTS IN THE CEILING AND / OR IN THE FLOOR AND TURBOMACHINE COMPRISING SUCH GRIDS.
US5224713A (en) * 1991-08-28 1993-07-06 General Electric Company Labyrinth seal with recirculating means for reducing or eliminating parasitic leakage through the seal
GB9607578D0 (en) * 1996-04-12 1996-06-12 Rolls Royce Plc Turbine rotor blades
EP0844369B1 (en) * 1996-11-23 2002-01-30 ROLLS-ROYCE plc A bladed rotor and surround assembly
DE59912323D1 (en) * 1998-12-24 2005-09-01 Alstom Technology Ltd Baden Turbine blade with actively cooled Deckbandelememt

Also Published As

Publication number Publication date
CA2562712A1 (en) 2004-11-18
JP4195882B2 (en) 2008-12-17
EA200501572A1 (en) 2006-08-25
HK1092853A1 (en) 2007-02-16
EA008156B1 (en) 2007-04-27
AU2003228590A1 (en) 2004-11-26
UA81314C2 (en) 2007-12-25
WO2004099572A1 (en) 2004-11-18
JP2006523792A (en) 2006-10-19
AU2003228590B2 (en) 2010-01-07
EP1623097A4 (en) 2012-06-27
CA2562712C (en) 2011-05-31
CN1788142A (en) 2006-06-14
BR0318261A (en) 2006-05-23
CN100386502C (en) 2008-05-07

Similar Documents

Publication Publication Date Title
US6478537B2 (en) Pre-segmented squealer tip for turbine blades
US20050186079A1 (en) Gas turbine tip shroud rails
US8549865B2 (en) Pressure-actuated plug
CN107002690A (en) Runner assembly for the turbogenerator including self-supporting rotor case
CN101644172A (en) Spring seal for blade dovetail
WO2012135512A1 (en) Turbine blade platform undercut
US7128522B2 (en) Leakage control in a gas turbine engine
US6632069B1 (en) Step of pressure of the steam and gas turbine with universal belt
EP3192971B1 (en) Gas turbine blade with platform cooling and method
US7549835B2 (en) Leakage flow control and seal wear minimization system for a turbine engine
US20190136700A1 (en) Ceramic matrix composite tip shroud assembly for gas turbines
US20070212214A1 (en) Segmented component seal
CN101624920B (en) For the labyrinth seal part of turbo machine dovetail and the method for seal clearance
RU2484258C2 (en) Device for flow movement in gas turbine engine
AU2003228590B2 (en) Steam/gas turbine pressure stage with universal shroud
CN207315450U (en) Supercritical carbon dioxide turbine step wheel disc
CN107605538A (en) Supercritical carbon dioxide turbine stepped wheel disc and design method thereof
US20200386116A1 (en) Turbocharger
US20040101410A1 (en) Axial flow fluid machine
KR100758725B1 (en) Steam / Gas Turbine Pressure Stages with Universal Shroud
HK1092853B (en) An improved shroud and sealing for a steam/gas turbine pressure stage

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20051114

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
A4 Supplementary search report drawn up and despatched

Effective date: 20120524

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 11/08 20060101ALI20120518BHEP

Ipc: F01D 5/18 20060101AFI20120518BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20120823