GB2006883A - Fan or Compressor Rotor Stage - Google Patents
Fan or Compressor Rotor StageInfo
- Publication number
- GB2006883A GB2006883A GB7841514A GB7841514A GB2006883A GB 2006883 A GB2006883 A GB 2006883A GB 7841514 A GB7841514 A GB 7841514A GB 7841514 A GB7841514 A GB 7841514A GB 2006883 A GB2006883 A GB 2006883A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fan
- spacer
- engaging
- compressor rotor
- rotor stage
- 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
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
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The stage comprises a rotor disc (12) from the periphery of which a row of angularly spaced apart rotor blades (13) is carried. To define the inner boundary of the flow passage through the stage, spacers (16) are provided between adjacent blades (13). Each spacer (16) has a rearward extremity (18) engaging the inward facing groove (19) of a thrust ring (20), and a forward extremity (23) engaging the forward face (24) of the disc to prevent rearward motion of the spacer. A recess 25 in the latter is engaged by retaining ring 27. <IMAGE>
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB7841514A GB2006883B (en) | 1977-10-27 | 1978-10-23 | Fan or compressor stage for a gas turbine engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4466677 | 1977-10-27 | ||
GB7841514A GB2006883B (en) | 1977-10-27 | 1978-10-23 | Fan or compressor stage for a gas turbine engine |
Publications (2)
Publication Number | Publication Date |
---|---|
GB2006883A true GB2006883A (en) | 1979-05-10 |
GB2006883B GB2006883B (en) | 1982-02-24 |
Family
ID=26265436
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB7841514A Expired GB2006883B (en) | 1977-10-27 | 1978-10-23 | Fan or compressor stage for a gas turbine engine |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB2006883B (en) |
Cited By (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4655687A (en) * | 1985-02-20 | 1987-04-07 | Rolls-Royce | Rotors for gas turbine engines |
FR2639402A1 (en) * | 1988-11-23 | 1990-05-25 | Snecma | TURBOMACHINE ROTOR WING DISC |
US5030063A (en) * | 1990-02-08 | 1991-07-09 | General Motors Corporation | Turbomachine rotor |
FR2669686A1 (en) * | 1990-11-28 | 1992-05-29 | Snecma | BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE. |
EP0502660A1 (en) * | 1991-03-04 | 1992-09-09 | General Electric Company | Platform assembly for attaching rotor blades to a rotor disk |
GB2257755A (en) * | 1991-07-17 | 1993-01-20 | Snecma | Interblade platform. |
US5222865A (en) * | 1991-03-04 | 1993-06-29 | General Electric Company | Platform assembly for attaching rotor blades to a rotor disk |
US5232346A (en) * | 1992-08-11 | 1993-08-03 | General Electric Company | Rotor assembly and platform spacer therefor |
US5244345A (en) * | 1991-01-15 | 1993-09-14 | Rolls-Royce Plc | Rotor |
WO1993021425A1 (en) * | 1992-04-16 | 1993-10-28 | Rolls-Royce Plc | Rotors for gas turbine engines |
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
US5281096A (en) * | 1992-09-10 | 1994-01-25 | General Electric Company | Fan assembly having lightweight platforms |
US5330324A (en) * | 1992-09-09 | 1994-07-19 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Annular gasket disposed at one axial extremity of a rotor and covering blade feet |
WO1994016200A1 (en) * | 1993-01-12 | 1994-07-21 | United Technologies Corporation | Free standing turbine disk sideplate assembly |
FR2706528A1 (en) * | 1993-06-10 | 1994-12-23 | Snecma | Separate inter-blade platform of turbine engine rotor blade disc. |
FR2710103A1 (en) * | 1993-09-16 | 1995-03-24 | Snecma | Turbomachine rotor flange and assembly of this flange to a rotor |
FR2715975A1 (en) * | 1994-02-10 | 1995-08-11 | Snecma | Rotor turbine rotor with axial or inclined emergent blade grooves. |
EP0677645A1 (en) * | 1994-03-19 | 1995-10-18 | ROLLS-ROYCE plc | A gas turbine engine fan blade assembly |
US6217283B1 (en) * | 1999-04-20 | 2001-04-17 | General Electric Company | Composite fan platform |
WO2001059263A2 (en) * | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Turbine blade arrangement |
FR2965843A1 (en) * | 2010-10-06 | 2012-04-13 | Snecma | ROTOR FOR TURBOMACHINE |
US8292586B2 (en) | 2008-02-18 | 2012-10-23 | Rolls-Royce Plc | Annulus filler |
US8777576B2 (en) | 2011-08-22 | 2014-07-15 | General Electric Company | Metallic fan blade platform |
JP2019512639A (en) * | 2016-03-21 | 2019-05-16 | サフラン エアークラフト エンジンズ | Wing pedestal and fan disk for aircraft turbine engines |
US20190218912A1 (en) * | 2018-01-16 | 2019-07-18 | Rolls-Royce Plc | Annulus filler |
WO2019224464A1 (en) * | 2018-05-23 | 2019-11-28 | Safran Aircraft Engines | Improved turbmachine fan disc |
EP4353952A1 (en) * | 2022-10-14 | 2024-04-17 | RTX Corporation | Retention of a fan blade of a gas turbine engine |
-
1978
- 1978-10-23 GB GB7841514A patent/GB2006883B/en not_active Expired
Cited By (46)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4655687A (en) * | 1985-02-20 | 1987-04-07 | Rolls-Royce | Rotors for gas turbine engines |
FR2639402A1 (en) * | 1988-11-23 | 1990-05-25 | Snecma | TURBOMACHINE ROTOR WING DISC |
EP0370899A1 (en) * | 1988-11-23 | 1990-05-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbine-bladed rotor disc |
US5049035A (en) * | 1988-11-23 | 1991-09-17 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Bladed disc for a turbomachine rotor |
US5030063A (en) * | 1990-02-08 | 1991-07-09 | General Motors Corporation | Turbomachine rotor |
EP0441424A1 (en) * | 1990-02-08 | 1991-08-14 | General Motors Corporation | Turbomachine rotor |
US5161949A (en) * | 1990-11-28 | 1992-11-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.M.C.A." | Rotor fitted with spacer blocks between the blades |
FR2669686A1 (en) * | 1990-11-28 | 1992-05-29 | Snecma | BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE. |
EP0488874A1 (en) * | 1990-11-28 | 1992-06-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Fan rotor with blades without platforms and fillers reconstructing the streamline profile |
US5244345A (en) * | 1991-01-15 | 1993-09-14 | Rolls-Royce Plc | Rotor |
US5222865A (en) * | 1991-03-04 | 1993-06-29 | General Electric Company | Platform assembly for attaching rotor blades to a rotor disk |
EP0502660A1 (en) * | 1991-03-04 | 1992-09-09 | General Electric Company | Platform assembly for attaching rotor blades to a rotor disk |
FR2679296A1 (en) * | 1991-07-17 | 1993-01-22 | Snecma | SEPARATE INTER-BEAM PLATFORM FOR ROTOR TURBOMACHINE ROTOR DISC. |
US5193982A (en) * | 1991-07-17 | 1993-03-16 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Separate inter-blade platform for a bladed rotor disk |
GB2257755B (en) * | 1991-07-17 | 1994-07-20 | Snecma | Separate inter-blade platform for a bladed rotor disc |
GB2257755A (en) * | 1991-07-17 | 1993-01-20 | Snecma | Interblade platform. |
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
WO1993021425A1 (en) * | 1992-04-16 | 1993-10-28 | Rolls-Royce Plc | Rotors for gas turbine engines |
US5466125A (en) * | 1992-04-16 | 1995-11-14 | Rolls-Royce Plc | Rotors for gas turbine engines |
US5232346A (en) * | 1992-08-11 | 1993-08-03 | General Electric Company | Rotor assembly and platform spacer therefor |
US5330324A (en) * | 1992-09-09 | 1994-07-19 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Annular gasket disposed at one axial extremity of a rotor and covering blade feet |
US5281096A (en) * | 1992-09-10 | 1994-01-25 | General Electric Company | Fan assembly having lightweight platforms |
WO1994016200A1 (en) * | 1993-01-12 | 1994-07-21 | United Technologies Corporation | Free standing turbine disk sideplate assembly |
FR2706528A1 (en) * | 1993-06-10 | 1994-12-23 | Snecma | Separate inter-blade platform of turbine engine rotor blade disc. |
US5421704A (en) * | 1993-06-10 | 1995-06-06 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Inter-blade platform for a bladed disc of a turbomachine rotor |
FR2710103A1 (en) * | 1993-09-16 | 1995-03-24 | Snecma | Turbomachine rotor flange and assembly of this flange to a rotor |
FR2715975A1 (en) * | 1994-02-10 | 1995-08-11 | Snecma | Rotor turbine rotor with axial or inclined emergent blade grooves. |
US5540552A (en) * | 1994-02-10 | 1996-07-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbine engine rotor having axial or inclined, issuing blade grooves |
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 |
US6217283B1 (en) * | 1999-04-20 | 2001-04-17 | General Electric Company | Composite fan platform |
US6726452B2 (en) | 2000-02-09 | 2004-04-27 | Siemens Aktiengesellschaft | Turbine blade arrangement |
EP1124038A1 (en) * | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Turbine blading |
WO2001059263A3 (en) * | 2000-02-09 | 2002-09-19 | Siemens Ag | Turbine blade arrangement |
WO2001059263A2 (en) * | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Turbine blade arrangement |
US8292586B2 (en) | 2008-02-18 | 2012-10-23 | Rolls-Royce Plc | Annulus filler |
FR2965843A1 (en) * | 2010-10-06 | 2012-04-13 | Snecma | ROTOR FOR TURBOMACHINE |
US8777576B2 (en) | 2011-08-22 | 2014-07-15 | General Electric Company | Metallic fan blade platform |
JP2019512639A (en) * | 2016-03-21 | 2019-05-16 | サフラン エアークラフト エンジンズ | Wing pedestal and fan disk for aircraft turbine engines |
US20190218912A1 (en) * | 2018-01-16 | 2019-07-18 | Rolls-Royce Plc | Annulus filler |
WO2019224464A1 (en) * | 2018-05-23 | 2019-11-28 | Safran Aircraft Engines | Improved turbmachine fan disc |
FR3081520A1 (en) * | 2018-05-23 | 2019-11-29 | Safran Aircraft Engines | IMPROVED TURBOMACHINE BLOWER DISK |
CN112189097A (en) * | 2018-05-23 | 2021-01-05 | 赛峰飞机发动机公司 | Improved turbine fan disk |
US11313239B2 (en) | 2018-05-23 | 2022-04-26 | Safran Aircraft Engines | Turbmachine fan disc |
EP4353952A1 (en) * | 2022-10-14 | 2024-04-17 | RTX Corporation | Retention of a fan blade of a gas turbine engine |
US12012857B2 (en) | 2022-10-14 | 2024-06-18 | Rtx Corporation | Platform for an airfoil of a gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
GB2006883B (en) | 1982-02-24 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |