GB2442695A - A blade mounting - Google Patents

A blade mounting Download PDF

Info

Publication number
GB2442695A
GB2442695A GB0802967A GB0802967A GB2442695A GB 2442695 A GB2442695 A GB 2442695A GB 0802967 A GB0802967 A GB 0802967A GB 0802967 A GB0802967 A GB 0802967A GB 2442695 A GB2442695 A GB 2442695A
Authority
GB
United Kingdom
Prior art keywords
blade
corners
aerofoil
root
angular
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Withdrawn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
GB0802967A
Other versions
GB0802967D0 (en
Inventor
Peter Rowland Beckford
Stephen John Booth
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 PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of GB0802967D0 publication Critical patent/GB0802967D0/en
Publication of GB2442695A publication Critical patent/GB2442695A/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Withdrawn legal-status Critical Current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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/313—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being perpendicular to each other
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other

Landscapes

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

Abstract

The angular nature of corners (3) to roots (2) of a conventional blade (1) used in a gas turbine engine has resulted in relatively thick fan casings in order to contain any blade fragments from these corners (3) as a result of blade failure. By angling the end face (26) of the root (22) such that it is nearer to perpendicular to an axis of curvature (27) for a blade (21) the corners (23) are reduced in their angular nature. In such circumstances the potential for penetration of a fan casing through impingement with such corners (23) is reduced and the fan casing thickness can more confidently be thinned reducing overall weight. Furthermore by appropriate profiling of an aerofoil (24) adjacent to the front and trailing edges (20) of the aerofoil about the root (22) and face (26) further reductions in angular parts of the blade can be achieved.
GB0802967A 2005-10-19 2006-09-22 A blade mounting Withdrawn GB2442695A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB0521242.8A GB0521242D0 (en) 2005-10-19 2005-10-19 A blade mounting
PCT/GB2006/003544 WO2007045815A1 (en) 2005-10-19 2006-09-22 A blade mounting

Publications (2)

Publication Number Publication Date
GB0802967D0 GB0802967D0 (en) 2008-03-26
GB2442695A true GB2442695A (en) 2008-04-09

Family

ID=35452013

Family Applications (2)

Application Number Title Priority Date Filing Date
GBGB0521242.8A Ceased GB0521242D0 (en) 2005-10-19 2005-10-19 A blade mounting
GB0802967A Withdrawn GB2442695A (en) 2005-10-19 2006-09-22 A blade mounting

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GBGB0521242.8A Ceased GB0521242D0 (en) 2005-10-19 2005-10-19 A blade mounting

Country Status (3)

Country Link
US (1) US20090136356A1 (en)
GB (2) GB0521242D0 (en)
WO (1) WO2007045815A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007051838A1 (en) * 2007-10-30 2009-05-07 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine blade root comprises two surfaces, which is auxiliary to bearing of gas turbine blade root, which is conjoined in right angle, and transient area of surfaces is formed with tapered and even edge
US9239062B2 (en) * 2012-09-10 2016-01-19 General Electric Company Low radius ratio fan for a gas turbine engine
US9677421B2 (en) * 2012-10-24 2017-06-13 United Technologies Corporation Gas turbine engine rotor drain feature
KR101882109B1 (en) * 2016-12-23 2018-07-25 두산중공업 주식회사 Gas turbine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1095392A (en) * 1953-12-01 1955-06-01 Csf Gas turbine blades
US3471127A (en) * 1966-12-08 1969-10-07 Gen Motors Corp Turbomachine rotor
US4050134A (en) * 1974-10-29 1977-09-27 Westinghouse Electric Corporation Method for removing rotatable blades without removing the casting of a turbine
GB2148404A (en) * 1983-10-19 1985-05-30 Gen Motors Corp End seal for turbine blade base
DE19705323A1 (en) * 1997-02-12 1998-08-27 Siemens Ag Turbo-machine blade
EP1219782A2 (en) * 2000-12-21 2002-07-03 United Technologies Corporation Bladed rotor assembly
US20030049130A1 (en) * 2001-09-13 2003-03-13 Miller Harold Edward Method and system for replacing a compressor blade
EP1355045A2 (en) * 2002-04-16 2003-10-22 United Technologies Corporation Bladed rotor for a gas turbine engine with a tiered blade to hub interface
EP1495829A1 (en) * 2003-07-10 2005-01-12 ROLLS-ROYCE plc Method of linear friction welding of blades to aerofoil blisks and blade having a root with a taper ratio less than 2

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1719415A (en) * 1927-09-14 1929-07-02 Westinghouse Electric & Mfg Co Turbine-blade attachment
BE755608A (en) * 1969-09-04 1971-02-15 Gen Electric COMPRESSOR BLADES
US3986793A (en) * 1974-10-29 1976-10-19 Westinghouse Electric Corporation Turbine rotating blade
US5067876A (en) * 1990-03-29 1991-11-26 General Electric Company Gas turbine bladed disk
US5088894A (en) * 1990-05-02 1992-02-18 Westinghouse Electric Corp. Turbomachine blade fastening
US5067877A (en) * 1990-09-11 1991-11-26 United Technologies Corporation Fan blade axial retention device
US5431542A (en) * 1994-04-29 1995-07-11 United Technologies Corporation Ramped dovetail rails for rotor blade assembly
US5599190A (en) * 1995-01-27 1997-02-04 The Whitaker Corporation Communication wiring system including a reconfigurable outlet assembly
US5836744A (en) * 1997-04-24 1998-11-17 United Technologies Corporation Frangible fan blade
JP4316168B2 (en) * 2001-08-30 2009-08-19 株式会社東芝 Method for selecting blade material and shape of steam turbine blade and steam turbine
US6846159B2 (en) * 2002-04-16 2005-01-25 United Technologies Corporation Chamfered attachment for a bladed rotor
GB0302116D0 (en) * 2003-01-30 2003-03-05 Rolls Royce Plc A rotor

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1095392A (en) * 1953-12-01 1955-06-01 Csf Gas turbine blades
US3471127A (en) * 1966-12-08 1969-10-07 Gen Motors Corp Turbomachine rotor
US4050134A (en) * 1974-10-29 1977-09-27 Westinghouse Electric Corporation Method for removing rotatable blades without removing the casting of a turbine
GB2148404A (en) * 1983-10-19 1985-05-30 Gen Motors Corp End seal for turbine blade base
DE19705323A1 (en) * 1997-02-12 1998-08-27 Siemens Ag Turbo-machine blade
EP1219782A2 (en) * 2000-12-21 2002-07-03 United Technologies Corporation Bladed rotor assembly
US20030049130A1 (en) * 2001-09-13 2003-03-13 Miller Harold Edward Method and system for replacing a compressor blade
EP1355045A2 (en) * 2002-04-16 2003-10-22 United Technologies Corporation Bladed rotor for a gas turbine engine with a tiered blade to hub interface
EP1495829A1 (en) * 2003-07-10 2005-01-12 ROLLS-ROYCE plc Method of linear friction welding of blades to aerofoil blisks and blade having a root with a taper ratio less than 2

Also Published As

Publication number Publication date
WO2007045815A1 (en) 2007-04-26
US20090136356A1 (en) 2009-05-28
GB0521242D0 (en) 2005-11-23
GB0802967D0 (en) 2008-03-26

Similar Documents

Publication Publication Date Title
PL1907671T3 (en) Gas-turbine blade ring
GB2434183A (en) Nonlinearly stacked low noise turbofan stator vane
DK201170467A (en) Wind turbine rotor blade assembly having an access window and related methods
RU2011106289A (en) A BLANK TURBINE FOR A TURBINE ROTOR, AT THIS SHOULDER INCLUDES A RIB
EP2108785A3 (en) Turbine blade and vane assembly with a ceramic platform
NO20053711L (en) Rotor blade for a wind power plant
ATE444896T1 (en) COVERING FOR A MAST FOR SUSPENSING A TURBINE ENGINE FROM AN AIRCRAFT WING
EP2535548A3 (en) Turbine section of high bypass turbofan
WO2007081347A3 (en) Ceramic matrix composite vane with chordwise stiffener
EP2199543A3 (en) Gas turbine engine airfoil
DK201170603A (en) Noise reducer for rotor blade in wind turbine
MX2010002579A (en) Seal coating between rotor blade and rotor disk slot in gas turbine engine.
EP4234947A3 (en) Total camber distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution
DE50214035D1 (en) Bearing ring for the storage of blade roots of adjustable stator blades in the high-pressure compressor of a gas turbine
MX2009009244A (en) Angled airfoil extension for fan blade.
MX2013013257A (en) Wind turbine rotor blade and method for installing a wind turbine rotor blade.
US20130149163A1 (en) Method for Reducing Stress on Blade Tips
DE602005007116D1 (en) Turbine blade and rotor of a gas turbine engine with such blades
NO20055599L (en) Rotor blade for a wind power plant
US10287891B2 (en) Radial lock for fan blade sheath
EP2159374A3 (en) Rotor blade
GB2427659B (en) A turbofan gas turbine engine fan blade and a turbofan gas turbine engine fan rotor arrangement
MX2008014120A (en) Rotor blade for a wind energy installation.
DE602005007115D1 (en) Turbine blade and rotor of a gas turbine engine with such blades
GB2442695A (en) A blade mounting

Legal Events

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