GB803137A - Improvements in or relating to axial-flow fluid machines for example turbines and compressors of gas-turbine engines - Google Patents
Improvements in or relating to axial-flow fluid machines for example turbines and compressors of gas-turbine enginesInfo
- Publication number
- GB803137A GB803137A GB22682/55A GB2268255A GB803137A GB 803137 A GB803137 A GB 803137A GB 22682/55 A GB22682/55 A GB 22682/55A GB 2268255 A GB2268255 A GB 2268255A GB 803137 A GB803137 A GB 803137A
- Authority
- GB
- United Kingdom
- Prior art keywords
- hollow
- platform structures
- wall
- interiors
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
803,137. Turbine and compressor stator vane assembly. ROLLS-ROYCE, Ltd. July 17, 1956 [Aug. 5, 1955], No. 22682/55. Class 110 (3). In an axial-flow fluid machine such as a turbine or compressor of a gas turbine engine, a stator assembly comprises a ring of hollow stator guide vanes which are secured at their ends in hollow, box-like inner and outer platform structures, the passages within the hollow guide vanes opening into the interiors of the box-like structures. The guide vanes are mounted in an outer casing by means of the outer platform structures and ducts are provided connecting the interiors of the outer platform structures to the exterior of the outer casing, and connecting the interiors of the inner platform structures to a chamber within the internal stationary structure of the machine. The gas turbine shown comprises a rotor disc 11 mounted at the end of a shaft 10 which rotates in a bearing 16. Gases from combustion equipment 15 are directed by inlet nozzle guide vanes 14 on to the rotor blades 12. The guide vanes 14 are hollow and they are arranged in groups of three, the outer ends of the vanes of each group being entered in slots in the inner wall 17 of an outer platform structure. The outer walls 18 of the outer platform structures have flanges 18a therearound, the flanges being connected to the inner walls 17. Each outer wall 18 is formed with a hollow boss 20 which is connected to a hollow boss 22 on the outer casing 13 by means of a tubular plug 21. The outer wall 18 is also formed with dogs 24 which engage dogs 25 formed on the inner surface of the outer casing 13 so as to locate the outer platform structure circumferentially. A shroud ring 27 for the rotor blades 12 engages a groove in the downstream edge of the wall 18 and is located axially and circumferentially with respect to the outer casing 13, the shroud ring thus locating the outer platform structure in an axial direction. The inner platform structures each comprise an outer wall 28, in which the inner end of the three vanes 14 are mounted, and an inner wall 29 having flanges 29a, the walls being connected together to form a boxlike structure. The inner walls 29 are each formed with a hollow boss 31 which engages a boss 35 on a ring member 34, and with an axial flange 46 which engages in a recess in a clamping ring 38. The outer walls 28 are each formed with an axial flange 44 which engages in a recess in a second clamping ring 37. Diaphragm members 32, 33 are secured between the clamping rings 37, 38 and the ring member 34, the parts being secured together by bolts. The diaphragm members 32, 33 have axiallydirected flanges 39, 40 which abut so as to hold the diaphragms in axially spaced relation. The annular chamber 47 formed by the diaphragms 32, 33, flanges 39, 40 and ring member 34 receives low pressure air through holes 51 in the diaphragm 32 or through holes 52 in the hollow shaft 10, air flowing through the holes 52 flowing through rotating seal 55 and holes 54 into the chamber. Air from the chamber 47 flows into the interiors of the inner platform structures, through the hollow vanes 14 to the interiors of the outer platform structures and thence to atmosphere. Instead of the arrangement shown, the outer platform structures may each constitute an outlet chamber from one hollow guide vane only.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB22682/55A GB803137A (en) | 1955-08-05 | 1955-08-05 | Improvements in or relating to axial-flow fluid machines for example turbines and compressors of gas-turbine engines |
US598909A US2836393A (en) | 1955-08-05 | 1956-07-19 | Stator construction for axial-flow fluid machine |
DER19397A DE1038343B (en) | 1955-08-05 | 1956-08-06 | Stator for axial turbo machines, especially gas turbines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB22682/55A GB803137A (en) | 1955-08-05 | 1955-08-05 | Improvements in or relating to axial-flow fluid machines for example turbines and compressors of gas-turbine engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB803137A true GB803137A (en) | 1958-10-22 |
Family
ID=10183408
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB22682/55A Expired GB803137A (en) | 1955-08-05 | 1955-08-05 | Improvements in or relating to axial-flow fluid machines for example turbines and compressors of gas-turbine engines |
Country Status (3)
Country | Link |
---|---|
US (1) | US2836393A (en) |
DE (1) | DE1038343B (en) |
GB (1) | GB803137A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1126196B (en) * | 1958-11-24 | 1962-03-22 | Rolls Royce | Gas turbine jet engine with bypass compressor |
DE1149944B (en) * | 1958-12-30 | 1963-06-06 | Gen Electric | Gas turbine engine with concentric air and hot gas ducts |
FR2556772A1 (en) * | 1983-12-15 | 1985-06-21 | Gen Electric | VARIABLE TIMING TURBINE BOLT SUPPORT |
FR2583820A1 (en) * | 1985-06-20 | 1986-12-26 | Snecma | Device for varying the passage cross-section of a turbine distributor |
EP0486082A1 (en) * | 1990-11-16 | 1992-05-20 | General Motors Corporation | Bearing support for a gas turbine |
EP0542403A1 (en) * | 1991-11-01 | 1993-05-19 | General Electric Company | Air transfer bushing |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3295823A (en) * | 1965-10-13 | 1967-01-03 | Raymond G H Waugh | Gas turbine cooling distribution system using the blade ring principle |
US3362681A (en) * | 1966-08-24 | 1968-01-09 | Gen Electric | Turbine cooling |
US3427000A (en) * | 1966-11-14 | 1969-02-11 | Westinghouse Electric Corp | Axial flow turbine structure |
US3529903A (en) * | 1968-11-29 | 1970-09-22 | Westinghouse Electric Corp | Nozzle blade structure |
US3850544A (en) * | 1973-11-02 | 1974-11-26 | Gen Electric | Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades |
US4126405A (en) * | 1976-12-16 | 1978-11-21 | General Electric Company | Turbine nozzle |
US4245951A (en) * | 1978-04-26 | 1981-01-20 | General Motors Corporation | Power turbine support |
SE512085C2 (en) * | 1998-05-28 | 2000-01-24 | Abb Ab | A rotor machine arrangement |
US6382906B1 (en) * | 2000-06-16 | 2002-05-07 | General Electric Company | Floating spoolie cup impingement baffle |
GB2398106B (en) * | 2003-01-13 | 2005-03-16 | Rolls Royce Plc | Gas turbine cooling system |
FR2862338B1 (en) * | 2003-11-17 | 2007-07-20 | Snecma Moteurs | DEVICE FOR CONNECTION BETWEEN A DISPENSER AND A SUPPLY ENCLOSURE FOR COOLANT FLUID INJECTORS IN A TURBOMACHINE |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2640319A (en) * | 1949-02-12 | 1953-06-02 | Packard Motor Car Co | Cooling of gas turbines |
US2741455A (en) * | 1950-06-29 | 1956-04-10 | Rolls Royce | Gas-turbine engines and nozzle-guidevane assemblies therefor |
GB701101A (en) * | 1950-06-29 | 1953-12-16 | Rolls Royce | Improvements in or relating to gas-turbine engines |
-
1955
- 1955-08-05 GB GB22682/55A patent/GB803137A/en not_active Expired
-
1956
- 1956-07-19 US US598909A patent/US2836393A/en not_active Expired - Lifetime
- 1956-08-06 DE DER19397A patent/DE1038343B/en active Pending
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1126196B (en) * | 1958-11-24 | 1962-03-22 | Rolls Royce | Gas turbine jet engine with bypass compressor |
DE1149944B (en) * | 1958-12-30 | 1963-06-06 | Gen Electric | Gas turbine engine with concentric air and hot gas ducts |
FR2556772A1 (en) * | 1983-12-15 | 1985-06-21 | Gen Electric | VARIABLE TIMING TURBINE BOLT SUPPORT |
FR2583820A1 (en) * | 1985-06-20 | 1986-12-26 | Snecma | Device for varying the passage cross-section of a turbine distributor |
EP0486082A1 (en) * | 1990-11-16 | 1992-05-20 | General Motors Corporation | Bearing support for a gas turbine |
EP0542403A1 (en) * | 1991-11-01 | 1993-05-19 | General Electric Company | Air transfer bushing |
Also Published As
Publication number | Publication date |
---|---|
DE1038343B (en) | 1958-09-04 |
US2836393A (en) | 1958-05-27 |
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