GB2442695A - A blade mounting - Google Patents
A blade mounting Download PDFInfo
- 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- Withdrawn
Links
- 239000012634 fragment Substances 0.000 abstract 1
- 230000035515 penetration Effects 0.000 abstract 1
- 230000009467 reduction Effects 0.000 abstract 1
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.
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)
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)
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)
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 |
-
2005
- 2005-10-19 GB GBGB0521242.8A patent/GB0521242D0/en not_active Ceased
-
2006
- 2006-09-22 GB GB0802967A patent/GB2442695A/en not_active Withdrawn
- 2006-09-22 WO PCT/GB2006/003544 patent/WO2007045815A1/en active Application Filing
- 2006-09-22 US US11/992,303 patent/US20090136356A1/en not_active Abandoned
Patent Citations (9)
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) |