GB806815A - Turbine blade shroud rings - Google Patents
Turbine blade shroud ringsInfo
- Publication number
- GB806815A GB806815A GB976056A GB976056A GB806815A GB 806815 A GB806815 A GB 806815A GB 976056 A GB976056 A GB 976056A GB 976056 A GB976056 A GB 976056A GB 806815 A GB806815 A GB 806815A
- Authority
- GB
- United Kingdom
- Prior art keywords
- sector
- casing
- shroud ring
- bolt
- sleeve
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
806,815. Turbine stator casings. NAPIER & SON Ltd., D. March 18, 1957 [March 28, 1956], No. 9760/56. Class 110 (3). A turbine comprises a casing having a shroud ring for a row of rotor blades disposed therein, the shroud ring being in the form of a series of separate arcuate, circumferentially-extending sections each connected to the casing by a device which allows for different relative thermal expansions of the associated parts whereby the radial clearance between the shroud ring and the rotor blades is maintained substantially at its designed value. The turbine shown comprises a rotor 11 carrying blades 13, and a casing 10 supporting inlet guide vanes 16 and interstage guide vanes 15, the casing also supporting a shroud ring which surrounds the tips of the rotor blades 13. The shroud ring comprises a series of arcuate sections 17 each of channel-section, as shown in Fig. 1 and closed at the ends as shown in Fig. 2. The closure 21 at one end of the section is bored and screwed and a hollow screwed bolt 25 is engaged therein, the bolt 25 being of steel having a high coefficient of thermal expansion (e.g. 22.7 Î 10<SP>-6</SP> per ‹ C.). The bolt 25 extends outwardly through an opening in the stator casing 10 and has secured to its outer end by means of a screwed collar 27 and cap 28 a sleeve 29 which is formed of steel having a low coefficient of thermal expansion (e.g. 4.8Î10<SP>-6</SP> per ‹ C.). The sleeve 29 is rigidly secured at its inner end to the casing 10. The bolt 25 and the sleeve 29 are a free fit on one another to permit relative movement. The adjacent ends of the shroud ring sectors 17 are stepped at 30, 31 so that the free end 31 of a sector is supported in the radial direction by the fixed end 30 of the adjacent sector with freedom for circumferential expansion. Alternatively, the adjacent ends of the sectors may be slotted tangentially and keys engaged in the slots so as to locate the free end of a sector radially but with freedom for circumferential expansion. A sheet-metal baffle 32 is mounted in each ring sector 17 to guide cooling air supplied from the space 33 through the passage 34 adjacent the outer surface of the sector, the air finally discharging into the working fluid stream through the opening 35. The bore in the end closure 21 of the sector permits hot gas from the working fluid stream to flow to the cavity 26 within the bolt 25. Specification 785,466 is referred to.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BE556215D BE556215A (en) | 1956-03-28 | ||
GB976056A GB806815A (en) | 1956-03-28 | 1956-03-28 | Turbine blade shroud rings |
CH338328D CH338328A (en) | 1956-03-28 | 1957-03-19 | Axial flow turbo machine |
DEN13451A DE1116685B (en) | 1956-03-28 | 1957-03-22 | Radial blade gap seal for hot steam or hot gas turbines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB976056A GB806815A (en) | 1956-03-28 | 1956-03-28 | Turbine blade shroud rings |
Publications (1)
Publication Number | Publication Date |
---|---|
GB806815A true GB806815A (en) | 1958-12-31 |
Family
ID=9878254
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB976056A Expired GB806815A (en) | 1956-03-28 | 1956-03-28 | Turbine blade shroud rings |
Country Status (4)
Country | Link |
---|---|
BE (1) | BE556215A (en) |
CH (1) | CH338328A (en) |
DE (1) | DE1116685B (en) |
GB (1) | GB806815A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2244523A (en) * | 1990-05-31 | 1991-12-04 | Gen Electric | Gas turbine shroud assembly |
US6179557B1 (en) | 1998-07-18 | 2001-01-30 | Rolls-Royce Plc | Turbine cooling |
GB2395756A (en) * | 2002-11-27 | 2004-06-02 | Rolls Royce Plc | Cooled gas turbine shroud |
RU2493388C1 (en) * | 2012-03-27 | 2013-09-20 | Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор" | Seal of gas turbine engine combustion chamber-to-stator joint |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1239889B (en) * | 1963-06-28 | 1967-05-03 | Licentia Gmbh | Inlet guide vane ring for axial turbines, in particular axial gas turbines, with radially resiliently pressed ring segments |
DE1286810B (en) * | 1963-11-19 | 1969-01-09 | Licentia Gmbh | Rotor blade radial gap cover ring of an axial turbine machine, in particular a gas turbine |
US3800864A (en) * | 1972-09-05 | 1974-04-02 | Gen Electric | Pin-fin cooling system |
FR2577281B1 (en) * | 1985-02-13 | 1987-03-20 | Snecma | TURBOMACHINE HOUSING ASSOCIATED WITH A DEVICE FOR ADJUSTING THE GAP BETWEEN MOBILE BLADES AND HOUSING |
FR2852053B1 (en) * | 2003-03-06 | 2007-12-28 | Snecma Moteurs | HIGH PRESSURE TURBINE FOR TURBOMACHINE |
RU2490478C2 (en) * | 2011-10-11 | 2013-08-20 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Turbomachine stator |
CN111396137A (en) * | 2020-04-29 | 2020-07-10 | 北京动力机械研究所 | High-efficient axial compressor turbine suitable for inert mixed working medium |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB629770A (en) * | 1947-11-21 | 1949-09-28 | Napier & Son Ltd | Improvements in or relating to sealing rings for turbines |
DE852789C (en) * | 1951-02-08 | 1952-10-20 | Maschf Augsburg Nuernberg Ag | Guide vane carrier for axial turbines |
US2858104A (en) * | 1954-02-04 | 1958-10-28 | A V Roe Canada Ltd | Adjustable gas turbine shroud ring segments |
-
0
- BE BE556215D patent/BE556215A/xx unknown
-
1956
- 1956-03-28 GB GB976056A patent/GB806815A/en not_active Expired
-
1957
- 1957-03-19 CH CH338328D patent/CH338328A/en unknown
- 1957-03-22 DE DEN13451A patent/DE1116685B/en active Pending
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2244523A (en) * | 1990-05-31 | 1991-12-04 | Gen Electric | Gas turbine shroud assembly |
US5127793A (en) * | 1990-05-31 | 1992-07-07 | General Electric Company | Turbine shroud clearance control assembly |
GB2244523B (en) * | 1990-05-31 | 1993-09-08 | Gen Electric | Turbine shroud assembly |
US6179557B1 (en) | 1998-07-18 | 2001-01-30 | Rolls-Royce Plc | Turbine cooling |
GB2395756A (en) * | 2002-11-27 | 2004-06-02 | Rolls Royce Plc | Cooled gas turbine shroud |
GB2395756B (en) * | 2002-11-27 | 2006-02-08 | Rolls Royce Plc | Cooled turbine assembly |
US7147431B2 (en) | 2002-11-27 | 2006-12-12 | Rolls-Royce Plc | Cooled turbine assembly |
RU2493388C1 (en) * | 2012-03-27 | 2013-09-20 | Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор" | Seal of gas turbine engine combustion chamber-to-stator joint |
Also Published As
Publication number | Publication date |
---|---|
BE556215A (en) | 1957-04-15 |
CH338328A (en) | 1959-05-15 |
DE1116685B (en) | 1961-11-09 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3730640A (en) | Seal ring for gas turbine | |
GB785466A (en) | Shroud ring construction for turbines and compressors | |
US4522557A (en) | Cooling device for movable turbine blade collars | |
US4314791A (en) | Variable stator cascades for axial-flow turbines of gas turbine engines | |
US4369016A (en) | Turbine intermediate case | |
US4425079A (en) | Air sealing for turbomachines | |
GB1199974A (en) | Turbine Blade Seal Assembly | |
US3825365A (en) | Cooled turbine rotor cylinder | |
GB617475A (en) | Improvements relating to gas-turbine engines | |
GB1270905A (en) | Cooling system for an axial flow elastic fluid utilizing machine | |
JPH0689653B2 (en) | Vane and packing clearance optimizer for gas turbine engine compressors | |
GB1263857A (en) | Improvements relating to pivotal guide vanes | |
GB804922A (en) | Improvements in or relating to axial-flow fluid machines for example compressors andturbines | |
GB1008526A (en) | Axial flow bladed rotor, e.g. for a turbine | |
US4804310A (en) | Clearance control apparatus for a bladed fluid flow machine | |
GB806815A (en) | Turbine blade shroud rings | |
GB904138A (en) | Improvements in or relating to stator structures, for example for axial flow gas turbine engines | |
GB1504813A (en) | Cooling apparatus for split shaft gas turbine | |
US2634090A (en) | Turbine apparatus | |
JPH06193403A (en) | Axial flow type turbomachinery | |
GB689270A (en) | Improvements in axial flow turbines or compressors | |
US3749512A (en) | Inlet structure for turbo machine | |
GB1335145A (en) | Turbine casing for a gas turbine engine | |
GB1063359A (en) | Jet propulsion engines | |
GB737473A (en) | Turbines and like machines having adjustable guide blades |