GB997852A - Aerofoil blade for use in a hot fluid stream - Google Patents
Aerofoil blade for use in a hot fluid streamInfo
- Publication number
- GB997852A GB997852A GB2395864A GB2395864A GB997852A GB 997852 A GB997852 A GB 997852A GB 2395864 A GB2395864 A GB 2395864A GB 2395864 A GB2395864 A GB 2395864A GB 997852 A GB997852 A GB 997852A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- leading edge
- fluid stream
- hot fluid
- ceramic material
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/284—Selection of ceramic materials
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Products (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
997,852. Turbine blades. ROLLS-ROYCE Ltd. June 9, 1964, No. 23958/64. Addition to 939,505. Heading F1T. The blade of the parent Specification is modified in that only part of its leading edge is made of ceramic material. As shown, a gas turbine engine nozzle guide vane 10 comprises a main, metal, body portion 13 provided with cooling fluid passages 15, 16, and a silicon nitride insert 12 cemented and, if necessary, keyed into a recess in the leading edge of the blade. The insert may extend only throughout the hottest part of the leading edge and, in this embodiment, is disposed in only the radially inner half of the blade, Fig. 1 (not shown). The ceramic material may incorporate a proportion of metal particles to improve its heat conductivity.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2395864A GB997852A (en) | 1964-06-09 | 1964-06-09 | Aerofoil blade for use in a hot fluid stream |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2395864A GB997852A (en) | 1964-06-09 | 1964-06-09 | Aerofoil blade for use in a hot fluid stream |
Publications (1)
Publication Number | Publication Date |
---|---|
GB997852A true GB997852A (en) | 1965-07-07 |
Family
ID=10204095
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2395864A Expired GB997852A (en) | 1964-06-09 | 1964-06-09 | Aerofoil blade for use in a hot fluid stream |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB997852A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6524074B2 (en) | 2000-07-27 | 2003-02-25 | Rolls-Royce Plc | Gas turbine engine blade |
-
1964
- 1964-06-09 GB GB2395864A patent/GB997852A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6524074B2 (en) | 2000-07-27 | 2003-02-25 | Rolls-Royce Plc | Gas turbine engine blade |
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