GB868788A - Improvements in gas turbine installations - Google Patents
Improvements in gas turbine installationsInfo
- Publication number
- GB868788A GB868788A GB35879/57A GB3587957A GB868788A GB 868788 A GB868788 A GB 868788A GB 35879/57 A GB35879/57 A GB 35879/57A GB 3587957 A GB3587957 A GB 3587957A GB 868788 A GB868788 A GB 868788A
- Authority
- GB
- United Kingdom
- Prior art keywords
- core
- blade
- alloy
- ducts
- metal
- 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
- F01D5/187—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
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- 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)
- Architecture (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
868,788. Coating with metals. POUIT, R. Nov. 18, 1957 [Nov. 20, 1956], No. 35879/57. Class 82(2) [Also in Group XXVI] In a gas turbine engine, at least one row of stator or rotor blades comprises blades having internal ducts for the passage of cooling fluid, each blade comprising a core formed of light metal or alloy having a relatively high coefficient of thermal conductivity, those surfaces of the blade which are exposed to the hot gas stream being protected by an adherent metallic surface layer having a coefficient of thermal conductivity which is appreciably less than that of the light metal or alloy forming the core of the blade. The invention is shown applied to turbine rotor blades which are mounted on a rotor disc 3, each blade comprising a core 4 provided with cooling fluid ducts 5 and an outer layer 6, cooling fluid such as air from a compressor driven by the turbine being supplied through duct 7 in the shaft and ducts 8 in the rotor disc to the ducts 5 in the blades. The core 4 may be a light alloy of aluminium or magnesium or of both of these metals, and the surface layer 6 may be a nickel base alloy. The core may be formed of a sintered complex of aluminium and alumina which has a very good thermal conductivity and low specific gravity. The outer layer 6 may be formed by a simple plating process for example by electrolysis, but is preferably formed so as to be secured to the blade core by metallic interdiffusion. The layer 6 may be applied in the form of a metallic compound such as a nickel salt which is acted on by suitable reactants, for example alkaline hypophosphites which ensures a deposition of protective metal and also the chemical formation of stable subjacent layers comprising nickel phosphites or phosphates which are poor heat conductors. The blade may be of aluminium and the surface layer produced by surface oxidation of the core. In another embodiment, the core of the blade is treated with a reactant which forms with the basic metal of the core (or at least one of its compounds in the case of an alloy) a compound of this basic metal which has a poorer conductivity than the basic metal or alloy proper, for example an oxide of the basic metals (or of at least one of its compounds in the case of an alloy) which is stable and adherant. The layer may be formed by the reaction of a suitable metalloid, for example phosphorous with the basic metal of the core.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR726045 | 1956-11-20 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB868788A true GB868788A (en) | 1961-05-25 |
Family
ID=8703957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB35879/57A Expired GB868788A (en) | 1956-11-20 | 1957-11-18 | Improvements in gas turbine installations |
Country Status (2)
| Country | Link |
|---|---|
| CH (1) | CH375955A (en) |
| GB (1) | GB868788A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3749514A (en) * | 1971-09-30 | 1973-07-31 | United Aircraft Corp | Blade attachment |
| GB2270126A (en) * | 1992-08-27 | 1994-03-02 | Inco Ltd | Cooling turbine blades |
| GB2432636A (en) * | 2005-11-29 | 2007-05-30 | Stephen Desmond Lewis | Supplying coolant to turbojet turbine blades |
| WO2010108879A1 (en) * | 2009-03-23 | 2010-09-30 | Alstom Technology Ltd | Gas turbine |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3211139C1 (en) * | 1982-03-26 | 1983-08-11 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Axial turbine blades, in particular axial turbine blades for gas turbine engines |
-
1957
- 1957-11-18 GB GB35879/57A patent/GB868788A/en not_active Expired
- 1957-11-19 CH CH5284357A patent/CH375955A/en unknown
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3749514A (en) * | 1971-09-30 | 1973-07-31 | United Aircraft Corp | Blade attachment |
| GB2270126A (en) * | 1992-08-27 | 1994-03-02 | Inco Ltd | Cooling turbine blades |
| GB2270126B (en) * | 1992-08-27 | 1995-08-02 | Inco Ltd | Gas turbine cooling |
| GB2432636A (en) * | 2005-11-29 | 2007-05-30 | Stephen Desmond Lewis | Supplying coolant to turbojet turbine blades |
| WO2010108879A1 (en) * | 2009-03-23 | 2010-09-30 | Alstom Technology Ltd | Gas turbine |
| EP2236746A1 (en) * | 2009-03-23 | 2010-10-06 | Alstom Technology Ltd | Gas turbine |
| US9341069B2 (en) | 2009-03-23 | 2016-05-17 | General Electric Technologyy Gmbh | Gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CH375955A (en) | 1964-03-15 |
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