GB1299904A - Transpiration cooled turbine blade with thin trailing edge - Google Patents
Transpiration cooled turbine blade with thin trailing edgeInfo
- Publication number
- GB1299904A GB1299904A GB6320069A GB6320069A GB1299904A GB 1299904 A GB1299904 A GB 1299904A GB 6320069 A GB6320069 A GB 6320069A GB 6320069 A GB6320069 A GB 6320069A GB 1299904 A GB1299904 A GB 1299904A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- turbine blade
- air
- trailing edge
- ribs
- 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
- F01D5/14—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
- F01D5/182—Transpiration cooling
- F01D5/183—Blade walls being porous
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1299904 Turbine blades CURTISS WRIGHT CORP 30 Dec 1969 63200/69 Heading FIT A gas turbine blade comprises a strut member 26 of generally aerofoil cross-section having a smooth trailing portion 21 and a forward portion with ribs 30 to which is secured a sheath 23 of porous material which terminates flush with the trailing portion 21. As shown the blade is a stator blade and the strut 26 has a chamber 27 to which cooling air is supplied through hollow trunnions 28, the air thence flowing through holes 31 to the recesses 29 between ribs 30. Adjacent recesses 29 may be inter-connected. The air then flows through the porous sheath 23, which is formed of metal mesh or sintered powdered metal, and over the blade exterior. The blade may be a rotor blade.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB6320069A GB1299904A (en) | 1969-12-30 | 1969-12-30 | Transpiration cooled turbine blade with thin trailing edge |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB6320069A GB1299904A (en) | 1969-12-30 | 1969-12-30 | Transpiration cooled turbine blade with thin trailing edge |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1299904A true GB1299904A (en) | 1972-12-13 |
Family
ID=10488858
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB6320069A Expired GB1299904A (en) | 1969-12-30 | 1969-12-30 | Transpiration cooled turbine blade with thin trailing edge |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1299904A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5102299A (en) * | 1986-11-10 | 1992-04-07 | The United States Of America As Represented By The Secretary Of The Air Force | Airfoil trailing edge cooling configuration |
US5405242A (en) * | 1990-07-09 | 1995-04-11 | United Technologies Corporation | Cooled vane |
US5720431A (en) * | 1988-08-24 | 1998-02-24 | United Technologies Corporation | Cooled blades for a gas turbine engine |
US5976337A (en) * | 1997-10-27 | 1999-11-02 | Allison Engine Company | Method for electrophoretic deposition of brazing material |
EP2472062A1 (en) * | 2010-12-28 | 2012-07-04 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine and airfoil |
US20200109635A1 (en) * | 2018-10-05 | 2020-04-09 | United Technologies Corporation | Composite cast porous metal turbine component |
-
1969
- 1969-12-30 GB GB6320069A patent/GB1299904A/en not_active Expired
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5102299A (en) * | 1986-11-10 | 1992-04-07 | The United States Of America As Represented By The Secretary Of The Air Force | Airfoil trailing edge cooling configuration |
US5720431A (en) * | 1988-08-24 | 1998-02-24 | United Technologies Corporation | Cooled blades for a gas turbine engine |
US5405242A (en) * | 1990-07-09 | 1995-04-11 | United Technologies Corporation | Cooled vane |
US5419039A (en) * | 1990-07-09 | 1995-05-30 | United Technologies Corporation | Method of making an air cooled vane with film cooling pocket construction |
US5976337A (en) * | 1997-10-27 | 1999-11-02 | Allison Engine Company | Method for electrophoretic deposition of brazing material |
EP2472062A1 (en) * | 2010-12-28 | 2012-07-04 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine and airfoil |
US8961133B2 (en) | 2010-12-28 | 2015-02-24 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine and cooled airfoil |
US20200109635A1 (en) * | 2018-10-05 | 2020-04-09 | United Technologies Corporation | Composite cast porous metal turbine component |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PLNP | Patent lapsed through nonpayment of renewal fees |