GB822172A - Improvements in or relating to the blade rotors for gas turbine engines - Google Patents
Improvements in or relating to the blade rotors for gas turbine enginesInfo
- Publication number
- GB822172A GB822172A GB20062/55A GB2006255A GB822172A GB 822172 A GB822172 A GB 822172A GB 20062/55 A GB20062/55 A GB 20062/55A GB 2006255 A GB2006255 A GB 2006255A GB 822172 A GB822172 A GB 822172A
- Authority
- GB
- United Kingdom
- Prior art keywords
- flanges
- screwed
- adjacent
- gas turbine
- compressor
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/063—Welded rotors
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
822,172. Turbine and compressor rotors. ROLLS-ROYCE Ltd. July 11, 1956 [July 11, 1955], No. 20062/55. Class 110 (3). A multi-stage, axial-flow compressor or turbine rotor for an aircraft gas turbine engine comprises a number of axially-spaced bladecarrying members such as discs or rings which have cylindrical flanges extending on either side thereof, the flanges being screwed and adjacent flanges being in screwed engagement one within the other and also abutting one another adjacent the screwed portions and being welded together adjacent the abutment. The gas turbine engine compressor rotor shown comprises discs 16, 17, 18 which carry rotor blades 15 and which are formed with cylindrical flanges 19, 20 on their upstream and downstream surfaces respectively. The flanges 20 are stepped inwardly so as to fit within the adjacent flanges 19 and the inter-engaging surfaces are screwed at 19a, 20b. The flanges 19, 20 are also formed with flanges 19c, 20c which abut and are welded together and with portions 19b, 20a which form a spigot and socket connection to locate the flanges radially. The flanges 19 are formed on their outer surfaces with ribs 19d which in the assembly cooperate with shroud members 13a mounted at the inner ends of the stator blades 13. The end disc 18 is formed with a conical portion 22 which is connected to the driving shaft 21. The flange 20 on the downstream face of the end disc 18 is formed with ribs 24 which co-operate with a flange 25 on the stator structure so as to form a labyrinth seal. The screw-threads are handed so that in operation the torque tends to tighten the connection.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB20062/55A GB822172A (en) | 1955-07-11 | 1955-07-11 | Improvements in or relating to the blade rotors for gas turbine engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB20062/55A GB822172A (en) | 1955-07-11 | 1955-07-11 | Improvements in or relating to the blade rotors for gas turbine engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB822172A true GB822172A (en) | 1959-10-21 |
Family
ID=10139743
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB20062/55A Expired GB822172A (en) | 1955-07-11 | 1955-07-11 | Improvements in or relating to the blade rotors for gas turbine engines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB822172A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2456835A1 (en) * | 1979-05-17 | 1980-12-12 | United Technologies Corp | ROTOR ASSEMBLY HAVING MULTI-STAGE DISC |
EP0604754A1 (en) * | 1992-11-26 | 1994-07-06 | ABBPATENT GmbH | Turbine rotor |
US5833244A (en) * | 1995-11-14 | 1998-11-10 | Rolls-Royce P L C | Gas turbine engine sealing arrangement |
FR3101106A1 (en) * | 2019-09-25 | 2021-03-26 | Safran Aircraft Engines | Turbine rotor of a turbomachine and turbomachine turbine equipped with such a rotor. |
-
1955
- 1955-07-11 GB GB20062/55A patent/GB822172A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2456835A1 (en) * | 1979-05-17 | 1980-12-12 | United Technologies Corp | ROTOR ASSEMBLY HAVING MULTI-STAGE DISC |
EP0604754A1 (en) * | 1992-11-26 | 1994-07-06 | ABBPATENT GmbH | Turbine rotor |
US5833244A (en) * | 1995-11-14 | 1998-11-10 | Rolls-Royce P L C | Gas turbine engine sealing arrangement |
FR3101106A1 (en) * | 2019-09-25 | 2021-03-26 | Safran Aircraft Engines | Turbine rotor of a turbomachine and turbomachine turbine equipped with such a rotor. |
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