EP1201880A3 - Cascade for turbomachines - Google Patents

Cascade for turbomachines Download PDF

Info

Publication number
EP1201880A3
EP1201880A3 EP01125191A EP01125191A EP1201880A3 EP 1201880 A3 EP1201880 A3 EP 1201880A3 EP 01125191 A EP01125191 A EP 01125191A EP 01125191 A EP01125191 A EP 01125191A EP 1201880 A3 EP1201880 A3 EP 1201880A3
Authority
EP
European Patent Office
Prior art keywords
grid
paddles
zone
offset
axial offset
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
EP01125191A
Other languages
German (de)
French (fr)
Other versions
EP1201880B1 (en
EP1201880A2 (en
Inventor
Andreas Dr. Fiala
Adam Heisler
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1201880A2 publication Critical patent/EP1201880A2/en
Publication of EP1201880A3 publication Critical patent/EP1201880A3/en
Application granted granted Critical
Publication of EP1201880B1 publication Critical patent/EP1201880B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes

Abstract

The paddle grid assembly for a turbo machine with an axial flow, and especially a gas turbine, has paddles (8) at the leading upstream grid (4) in an initial coherent array or in separate sectors in a part-zone at the grid periphery, in succession at an equal axial offset ( DELTA m). The axial offset depends on the ratio of the number of paddles at the first and second grid. Where the first grid has more paddles, the effective outflow cross section (Aeff) is increased and vice versa. The paddles at the leading grid are positioned in a second part-zone at an equal or variable axial offset alignment against the offset of the first group.
EP01125191A 2000-10-27 2001-10-24 Cascade for turbomachines Expired - Lifetime EP1201880B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10053361 2000-10-27
DE10053361A DE10053361C1 (en) 2000-10-27 2000-10-27 Blade grid arrangement for turbomachinery

Publications (3)

Publication Number Publication Date
EP1201880A2 EP1201880A2 (en) 2002-05-02
EP1201880A3 true EP1201880A3 (en) 2003-07-02
EP1201880B1 EP1201880B1 (en) 2004-09-22

Family

ID=7661316

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01125191A Expired - Lifetime EP1201880B1 (en) 2000-10-27 2001-10-24 Cascade for turbomachines

Country Status (5)

Country Link
US (1) US6540478B2 (en)
EP (1) EP1201880B1 (en)
AT (1) ATE277277T1 (en)
CA (1) CA2360395C (en)
DE (2) DE10053361C1 (en)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2401654B (en) * 2003-05-14 2006-04-19 Rolls Royce Plc A stator vane assembly for a turbomachine
DE10357075B4 (en) * 2003-12-06 2006-01-12 Dornier Gmbh Method for noise reduction of turbomachinery
DE102004059882A1 (en) * 2004-12-10 2006-06-22 Rolls-Royce Deutschland Ltd & Co Kg Lean pre-mixing burner for combustion chamber, has main air-ring channel with integrated swirl units that are designed as aerodynamic profiled and/or formed air guide vanes that divert air stream into channel in preset angle
ES2310307T3 (en) * 2005-05-10 2009-01-01 Mtu Aero Engines Gmbh PROCEDURE FOR THE OPTIMIZATION OF THE CURRENT IN MOTORS OF TURBOPROPULSION OF VARIOUS PHASES.
DE102005048982A1 (en) 2005-10-13 2007-04-19 Mtu Aero Engines Gmbh Apparatus and method for axially displacing a turbine rotor
CN100376765C (en) * 2005-10-28 2008-03-26 中国科学院工程热物理研究所 Three-D sequential effect maximization method for multi-stage turbomachine
FR2925106B1 (en) * 2007-12-14 2010-01-22 Snecma METHOD FOR DESIGNING A TURBOMACHINE MULTI-STAGE TURBINE
US8540490B2 (en) * 2008-06-20 2013-09-24 General Electric Company Noise reduction in a turbomachine, and a related method thereof
US20090317237A1 (en) * 2008-06-20 2009-12-24 General Electric Company System and method for reduction of unsteady pressures in turbomachinery
US20100054929A1 (en) * 2008-09-04 2010-03-04 General Electric Company Turbine airfoil clocking
DE102008049358A1 (en) * 2008-09-29 2010-04-01 Mtu Aero Engines Gmbh Axial flow machine with asymmetric compressor inlet guide
DE102008058014A1 (en) * 2008-11-19 2010-05-20 Rolls-Royce Deutschland Ltd & Co Kg Multiblade variable stator unit of a fluid flow machine
US8439626B2 (en) * 2008-12-29 2013-05-14 General Electric Company Turbine airfoil clocking
US20130081402A1 (en) * 2011-10-03 2013-04-04 General Electric Company Turbomachine having a gas flow aeromechanic system and method
US20130209216A1 (en) * 2012-02-09 2013-08-15 General Electric Company Turbomachine including flow improvement system
US20140068938A1 (en) * 2012-09-10 2014-03-13 General Electric Company Method of clocking a turbine with skewed wakes
US9435221B2 (en) 2013-08-09 2016-09-06 General Electric Company Turbomachine airfoil positioning
EP3047116B1 (en) * 2013-09-16 2021-04-14 Raytheon Technologies Corporation Variable area turbine vane row assembly
DE102014204346A1 (en) 2014-03-10 2015-09-10 Rolls-Royce Deutschland Ltd & Co Kg Method for producing a double-row paddle wheel for a turbomachine and double-row paddle wheel
US10378554B2 (en) 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane
US10145301B2 (en) 2014-09-23 2018-12-04 Pratt & Whitney Canada Corp. Gas turbine engine inlet
US9957807B2 (en) 2015-04-23 2018-05-01 Pratt & Whitney Canada Corp. Rotor assembly with scoop
US9938848B2 (en) 2015-04-23 2018-04-10 Pratt & Whitney Canada Corp. Rotor assembly with wear member
US20180010459A1 (en) * 2016-01-11 2018-01-11 United Technologies Corporation Low energy wake stage
US10724540B2 (en) 2016-12-06 2020-07-28 Pratt & Whitney Canada Corp. Stator for a gas turbine engine fan
US10690146B2 (en) 2017-01-05 2020-06-23 Pratt & Whitney Canada Corp. Turbofan nacelle assembly with flow disruptor

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US910266A (en) * 1906-12-17 1909-01-19 Giuseppe Belluzzo Elastic-fluid turbine.
DE439905C (en) * 1927-01-22 Georg Forner Dr Ing Control device for steam turbines
FR1200484A (en) * 1958-06-26 1959-12-22 Alsthom Cgee Water drainage device in steam turbines
US3347520A (en) * 1966-07-12 1967-10-17 Jerzy A Oweczarek Turbomachine blading

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE433183C (en) * 1924-05-16 1926-08-24 Erste Bruenner Maschinen Fab Blades for axial steam or gas turbines
DE1033677B (en) * 1957-10-31 1958-07-10 Maschf Augsburg Nuernberg Ag Diffuser with adjustable blades for turbines and compressors, especially for gas turbines
CH557468A (en) * 1973-04-30 1974-12-31 Bbc Brown Boveri & Cie TURBINE OF AXIAL DESIGN.
SE500471C2 (en) * 1991-07-09 1994-07-04 Flaekt Ab Guide device in an axial fan
US5486091A (en) 1994-04-19 1996-01-23 United Technologies Corporation Gas turbine airfoil clocking
US6402458B1 (en) * 2000-08-16 2002-06-11 General Electric Company Clock turbine airfoil cooling

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE439905C (en) * 1927-01-22 Georg Forner Dr Ing Control device for steam turbines
US910266A (en) * 1906-12-17 1909-01-19 Giuseppe Belluzzo Elastic-fluid turbine.
FR1200484A (en) * 1958-06-26 1959-12-22 Alsthom Cgee Water drainage device in steam turbines
US3347520A (en) * 1966-07-12 1967-10-17 Jerzy A Oweczarek Turbomachine blading

Also Published As

Publication number Publication date
DE10053361C1 (en) 2002-06-06
CA2360395C (en) 2010-03-23
ATE277277T1 (en) 2004-10-15
CA2360395A1 (en) 2002-04-27
US6540478B2 (en) 2003-04-01
US20020057966A1 (en) 2002-05-16
DE50103734D1 (en) 2004-10-28
EP1201880B1 (en) 2004-09-22
EP1201880A2 (en) 2002-05-02

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