GB1331209A - Bladed rotors for fluid flow machines - Google Patents
Bladed rotors for fluid flow machinesInfo
- Publication number
- GB1331209A GB1331209A GB1331209DA GB1331209A GB 1331209 A GB1331209 A GB 1331209A GB 1331209D A GB1331209D A GB 1331209DA GB 1331209 A GB1331209 A GB 1331209A
- Authority
- GB
- United Kingdom
- Prior art keywords
- spacer
- walls
- secured
- fluid flow
- flanges
- 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.)
- Expired
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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1331209 Turbomachine rotors DEFENCE SECRETARY OF STATE FOR 27 July 1972 35114/72 Addition to 1232506 Heading FIT The rotor blade spacer described in Specification 1232506 is modified by the provision of axially extending flanges 40, 41 on radial bracing walls 24, 25 respectively, the flanges co-operating with elastomer sealing strips 45 secured to the flanks of circumferentially adjacent blades 12. The walls 24, 25 extend the full axial length of the spacer. An additional glass reinforced plastics reinforcing wall 44 is provided. Each spacer may be secured to rotor 33, e.g. the front fan of a gas turbine ducted fan engine, by a bolt 32 located in a recess 30 of a mushroom shaped member 31 bonded within holes 38, 38' in walls 15, 16 respectively. The upstream end 22 of each spacer fits into a nose cone 35.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB5274769 | 1969-10-28 | ||
GB3511472 | 1972-07-27 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1331209A true GB1331209A (en) | 1973-09-26 |
Family
ID=26262580
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1331209D Expired GB1331209A (en) | 1969-10-28 | 1972-07-27 | Bladed rotors for fluid flow machines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1331209A (en) |
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2654773A1 (en) * | 1989-11-22 | 1991-05-24 | Snecma | AXIAL FLOW TURBOMACHINE ROTOR. |
GB2257755A (en) * | 1991-07-17 | 1993-01-20 | Snecma | Interblade platform. |
WO1993022539A1 (en) * | 1992-05-07 | 1993-11-11 | Rolls-Royce Plc | Rotors for gas turbine engines |
FR2706528A1 (en) * | 1993-06-10 | 1994-12-23 | Snecma | Separate inter-blade platform of turbine engine rotor blade disc. |
FR2716502A1 (en) * | 1994-02-23 | 1995-08-25 | Snecma | Sealing between vanes and intermediate platforms. |
EP0677645A1 (en) * | 1994-03-19 | 1995-10-18 | ROLLS-ROYCE plc | A gas turbine engine fan blade assembly |
WO1997044570A1 (en) * | 1996-05-20 | 1997-11-27 | Pratt & Whitney Canada Inc. | Gas turbine engine shroud seals |
US8070438B2 (en) | 2006-07-21 | 2011-12-06 | Rolls-Royce Plc | Fan blade for a gas turbine engine |
US8287239B2 (en) | 2008-03-07 | 2012-10-16 | Rolls-Royce Plc | Annulus filler |
EP2108786A3 (en) * | 2008-04-07 | 2012-12-26 | Rolls-Royce plc | Aeroengine fan assembly |
US8425192B2 (en) | 2009-05-18 | 2013-04-23 | Rolls-Royce Plc | Annulus filler |
US8596981B2 (en) | 2009-06-23 | 2013-12-03 | Rolls-Royce Plc | Annulus filler for a gas turbine engine |
US8636474B2 (en) | 2009-08-12 | 2014-01-28 | Rolls-Royce Plc | Rotor assembly for a gas turbine |
US8864451B2 (en) | 2010-03-23 | 2014-10-21 | Rolls-Royce Plc | Interstage seal |
EP2932047A4 (en) * | 2012-12-14 | 2015-12-09 | United Technologies Corp | Gas turbine engine fan blade platform seal |
FR3052822A1 (en) * | 2016-06-16 | 2017-12-22 | Snecma | TURBOMACHINE DAWN EQUIPPED WITH AN ELASTOMER SEAL |
FR3093534A1 (en) * | 2019-03-07 | 2020-09-11 | Safran Aircraft Engines | Aeronautical turbomachine fan platform |
EP3851644A1 (en) * | 2020-01-17 | 2021-07-21 | Raytheon Technologies Corporation | Turbine fan fairing platform with protective surface |
CN114127425A (en) * | 2019-06-26 | 2022-03-01 | 赛峰飞机发动机公司 | Inter-blade platform with sacrificial box section |
-
1972
- 1972-07-27 GB GB1331209D patent/GB1331209A/en not_active Expired
Cited By (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2654773A1 (en) * | 1989-11-22 | 1991-05-24 | Snecma | AXIAL FLOW TURBOMACHINE ROTOR. |
EP0429353A1 (en) * | 1989-11-22 | 1991-05-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Axial turbomachine |
US5145319A (en) * | 1989-11-22 | 1992-09-08 | Societe Nationale D'etude Et De Construction De Moteurs D'aviations S.N.E.M.C.A. | Axial flow turbomachine rotor |
GB2257755A (en) * | 1991-07-17 | 1993-01-20 | Snecma | Interblade platform. |
GB2257755B (en) * | 1991-07-17 | 1994-07-20 | Snecma | Separate inter-blade platform for a bladed rotor disc |
WO1993022539A1 (en) * | 1992-05-07 | 1993-11-11 | Rolls-Royce Plc | Rotors for gas turbine engines |
US5464326A (en) * | 1992-05-07 | 1995-11-07 | Rolls-Royce, Plc | Rotors for gas turbine engines |
FR2706528A1 (en) * | 1993-06-10 | 1994-12-23 | Snecma | Separate inter-blade platform of turbine engine rotor blade disc. |
EP0669451A1 (en) * | 1994-02-23 | 1995-08-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Seal between the blades and the intermediate platforms |
FR2716502A1 (en) * | 1994-02-23 | 1995-08-25 | Snecma | Sealing between vanes and intermediate platforms. |
US5520514A (en) * | 1994-02-23 | 1996-05-28 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Sealing lining between vanes and intermediate platforms |
EP0677645A1 (en) * | 1994-03-19 | 1995-10-18 | ROLLS-ROYCE plc | A gas turbine engine fan blade assembly |
US5580217A (en) * | 1994-03-19 | 1996-12-03 | Rolls-Royce Plc | Gas turbine engine fan blade assembly |
WO1997044570A1 (en) * | 1996-05-20 | 1997-11-27 | Pratt & Whitney Canada Inc. | Gas turbine engine shroud seals |
US8070438B2 (en) | 2006-07-21 | 2011-12-06 | Rolls-Royce Plc | Fan blade for a gas turbine engine |
US8287239B2 (en) | 2008-03-07 | 2012-10-16 | Rolls-Royce Plc | Annulus filler |
EP2108786A3 (en) * | 2008-04-07 | 2012-12-26 | Rolls-Royce plc | Aeroengine fan assembly |
US8535013B2 (en) | 2008-04-07 | 2013-09-17 | Rolls-Royce Plc | Aeroengine fan assembly |
US8425192B2 (en) | 2009-05-18 | 2013-04-23 | Rolls-Royce Plc | Annulus filler |
US8596981B2 (en) | 2009-06-23 | 2013-12-03 | Rolls-Royce Plc | Annulus filler for a gas turbine engine |
EP2267277A3 (en) * | 2009-06-23 | 2017-11-29 | Rolls-Royce plc | Annulus filler and method of mounting the annulus filler to a rotor disc of a gas turbine engine |
US8636474B2 (en) | 2009-08-12 | 2014-01-28 | Rolls-Royce Plc | Rotor assembly for a gas turbine |
US8864451B2 (en) | 2010-03-23 | 2014-10-21 | Rolls-Royce Plc | Interstage seal |
EP2932047A4 (en) * | 2012-12-14 | 2015-12-09 | United Technologies Corp | Gas turbine engine fan blade platform seal |
GB2552085A (en) * | 2016-06-16 | 2018-01-10 | Safran Aircraft Engines | A turbine engine blade fitted with an elastomer gasket |
FR3052822A1 (en) * | 2016-06-16 | 2017-12-22 | Snecma | TURBOMACHINE DAWN EQUIPPED WITH AN ELASTOMER SEAL |
US10689996B2 (en) | 2016-06-16 | 2020-06-23 | Safran Aircraft Engines | Turbomachine blade fitted with an elastomer gasket |
GB2552085B (en) * | 2016-06-16 | 2020-11-11 | Safran Aircraft Engines | A turbomachine blade fitted with an elastomer gasket |
FR3093534A1 (en) * | 2019-03-07 | 2020-09-11 | Safran Aircraft Engines | Aeronautical turbomachine fan platform |
CN114127425A (en) * | 2019-06-26 | 2022-03-01 | 赛峰飞机发动机公司 | Inter-blade platform with sacrificial box section |
CN114127425B (en) * | 2019-06-26 | 2023-08-29 | 赛峰飞机发动机公司 | Inter-blade platform with sacrificial tank sections |
EP3851644A1 (en) * | 2020-01-17 | 2021-07-21 | Raytheon Technologies Corporation | Turbine fan fairing platform with protective surface |
US11268396B2 (en) | 2020-01-17 | 2022-03-08 | Raytheon Technologies Corporation | Turbine fan fairing platform with protective surface |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB1331209A (en) | Bladed rotors for fluid flow machines | |
GB1318654A (en) | Bladed rotors | |
GB1063918A (en) | Axial-flow turbine rotors | |
GB1113087A (en) | Gas turbine power plant | |
GB1373898A (en) | Gas turbine nozzle vane structure | |
GB1093568A (en) | Improvements in or relating to bladed rotors such as compressor rotors | |
GB1008526A (en) | Axial flow bladed rotor, e.g. for a turbine | |
GB1491556A (en) | Rotor blades for turbomachines | |
GB1387480A (en) | Energy transfer machine | |
GB1118898A (en) | Fluid flow machine | |
GB1314853A (en) | Stator blading for turbomachinery | |
GB1251312A (en) | ||
GB689270A (en) | Improvements in axial flow turbines or compressors | |
GB1276100A (en) | Bladed member for a fluid flow machine | |
GB931904A (en) | Fluid flow machine | |
GB1127269A (en) | By-pass gas turbine engine having a compressor and fan exit guide vane assembly | |
GB1073490A (en) | Centrifugal compressor impellers | |
GB712523A (en) | Improvements in or relating to guide vane assemblies in annular fluid ducts | |
GB1524956A (en) | Gas tubine engine | |
GB838602A (en) | Improvements in or relating to gas turbine plant | |
GB1121194A (en) | Bladed rotor for a fluid flow machine | |
GB1065278A (en) | Improvements in or relating to compressors for gas turbine jet propulsion engines | |
GB981476A (en) | Gas turbine engine vane assembly | |
GB765345A (en) | Improvements relating to the construction of axial flow fans | |
GB597165A (en) | Improvements relating to the construction of stator elements of turbines, compressors or like machines |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PLNP | Patent lapsed through nonpayment of renewal fees |