GB201303700D0 - Rotating turbomachine component having a tip leakage flow guide - Google Patents

Rotating turbomachine component having a tip leakage flow guide

Info

Publication number
GB201303700D0
GB201303700D0 GBGB1303700.7A GB201303700A GB201303700D0 GB 201303700 D0 GB201303700 D0 GB 201303700D0 GB 201303700 A GB201303700 A GB 201303700A GB 201303700 D0 GB201303700 D0 GB 201303700D0
Authority
GB
United Kingdom
Prior art keywords
leakage flow
flow guide
turbomachine component
rotating turbomachine
tip leakage
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Withdrawn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
GBGB1303700.7A
Other versions
GB2501169A (en
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB201303700D0 publication Critical patent/GB201303700D0/en
Publication of GB2501169A publication Critical patent/GB2501169A/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Withdrawn legal-status Critical Current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
    • F01D5/22—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
    • 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
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A rotating turbomachine component includes a base portion and an airfoil portion extending from the base portion. The airfoil portion includes a first end connected to the base portion and a tip end portion that is cantilevered from the base portion. A tip leakage flow guide is provided at the tip end portion of the airfoil portion. The tip leakage flow guide includes one or more turning vane members configured and disposed to guide a leakage flow from the tip end portion at a flow angle that substantially coincides with a flow angle of gases flowing downstream from the rotating turbomachine component.
GB1303700.7A 2012-03-01 2013-03-01 Rotating turbomachine component, eg turbine blade, having a tip leakage flow guide Withdrawn GB2501169A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/409,637 US20130230379A1 (en) 2012-03-01 2012-03-01 Rotating turbomachine component having a tip leakage flow guide

Publications (2)

Publication Number Publication Date
GB201303700D0 true GB201303700D0 (en) 2013-04-17
GB2501169A GB2501169A (en) 2013-10-16

Family

ID=48142266

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1303700.7A Withdrawn GB2501169A (en) 2012-03-01 2013-03-01 Rotating turbomachine component, eg turbine blade, having a tip leakage flow guide

Country Status (6)

Country Link
US (1) US20130230379A1 (en)
JP (1) JP2013181543A (en)
CN (1) CN103291376A (en)
DE (1) DE102013101902A1 (en)
GB (1) GB2501169A (en)
RU (1) RU2013108927A (en)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5591042B2 (en) * 2010-09-17 2014-09-17 三菱重工業株式会社 Turbine
US9951629B2 (en) 2012-07-03 2018-04-24 United Technologies Corporation Tip leakage flow directionality control
US9957817B2 (en) 2012-07-03 2018-05-01 United Technologies Corporation Tip leakage flow directionality control
US9777582B2 (en) 2012-07-03 2017-10-03 United Technologies Corporation Tip leakage flow directionality control
JP5985351B2 (en) * 2012-10-25 2016-09-06 三菱日立パワーシステムズ株式会社 Axial flow turbine
US10247025B2 (en) * 2013-04-03 2019-04-02 Mitsubishi Heavy Industries, Ltd. Rotating machine
JP2015094220A (en) * 2013-11-08 2015-05-18 三菱日立パワーシステムズ株式会社 Axial flow turbine
CN104454026A (en) * 2014-11-09 2015-03-25 沈阳黎明航空发动机(集团)有限责任公司 Zigzag-shroud of aero-engine rotor vane
BR112017021169B1 (en) 2015-04-08 2022-11-22 Horton, Inc FAN BLADE AND AXIAL FLOW FAN OPERATION METHOD
CN104847416A (en) * 2015-04-09 2015-08-19 上海理工大学 Impeller top surrounding band and turbine
CN104929699B (en) * 2015-06-05 2016-05-11 中国民用航空飞行学院 A kind of booster-type comb tooth of obturaging
EP3147460A1 (en) * 2015-09-23 2017-03-29 General Electric Technology GmbH Axial flow turbine
GB201519869D0 (en) * 2015-11-11 2015-12-23 Rolls Royce Plc Shrouded turbine blade
WO2017200549A1 (en) * 2016-05-20 2017-11-23 Siemens Aktiengesellschaft Tip shroud with a fence feature for discouraging pitch-wise over-tip leakage flow
US10822977B2 (en) * 2016-11-30 2020-11-03 General Electric Company Guide vane assembly for a rotary machine and methods of assembling the same
JP6986426B2 (en) * 2017-11-29 2021-12-22 三菱重工業株式会社 Turbine
JP2021050688A (en) 2019-09-26 2021-04-01 川崎重工業株式会社 Turbine blade
FR3125085A1 (en) * 2021-07-12 2023-01-13 Safran Aircraft Engines Turbomachine blade
CN114320487A (en) * 2022-01-07 2022-04-12 中国航发贵阳发动机设计研究所 Grate tooth sealing structure and method suitable for same
CN115324657A (en) * 2022-10-12 2022-11-11 中国航发四川燃气涡轮研究院 Turbine working blade shroud cooling structure

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US881474A (en) * 1906-08-14 1908-03-10 Belliss & Morcom Ltd Turbine-motor.
GB1423833A (en) * 1972-04-20 1976-02-04 Rolls Royce Rotor blades for fluid flow machines
JPS5812602U (en) * 1981-07-16 1983-01-26 株式会社東芝 turbine moving blade
DE3308140C2 (en) * 1983-03-08 1985-12-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Multi-stage gas turbine
DE3523469A1 (en) * 1985-07-01 1987-01-08 Bbc Brown Boveri & Cie Contact-free controlled-gap seal for turbo-machines
US5074752A (en) * 1990-08-06 1991-12-24 General Electric Company Gas turbine outlet guide vane mounting assembly
US5234318A (en) * 1993-01-22 1993-08-10 Brandon Ronald E Clip-on radial tip seals for steam and gas turbines
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
US6027306A (en) * 1997-06-23 2000-02-22 General Electric Company Turbine blade tip flow discouragers
GB2340189A (en) * 1998-08-04 2000-02-16 Siemens Plc A turbomachine shroud seal having baffles
FR2825411B1 (en) * 2001-05-31 2003-09-19 Snecma Moteurs TURBINE DAWN WITH SEALING LECHETTE
JP2004011553A (en) * 2002-06-07 2004-01-15 Mitsubishi Heavy Ind Ltd Axial flow type turbo machine
US7270519B2 (en) * 2002-11-12 2007-09-18 General Electric Company Methods and apparatus for reducing flow across compressor airfoil tips
WO2004113770A2 (en) * 2003-06-20 2004-12-29 Elliott Company Swirl-reversal abradable labyrinth seal
US6851931B1 (en) * 2003-08-13 2005-02-08 General Electric Company Turbine bucket tip shroud edge profile
GB2417053B (en) * 2004-08-11 2006-07-12 Rolls Royce Plc Turbine
JP2007321721A (en) * 2006-06-05 2007-12-13 Toshiba Corp Axial flow turbine stage and axial flow turbine
JP2010169047A (en) * 2009-01-26 2010-08-05 Toshiba Corp Axial flow turbine
DE102009040758A1 (en) * 2009-09-10 2011-03-17 Mtu Aero Engines Gmbh Deflection device for a leakage current in a gas turbine and gas turbine
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
JP2011106474A (en) * 2011-03-04 2011-06-02 Toshiba Corp Axial flow turbine stage and axial flow turbine

Also Published As

Publication number Publication date
JP2013181543A (en) 2013-09-12
GB2501169A (en) 2013-10-16
US20130230379A1 (en) 2013-09-05
DE102013101902A1 (en) 2013-09-05
CN103291376A (en) 2013-09-11
RU2013108927A (en) 2014-09-10

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)