GB722341A - Improvements relating to turbine blades - Google Patents
Improvements relating to turbine bladesInfo
- Publication number
- GB722341A GB722341A GB714952A GB714952A GB722341A GB 722341 A GB722341 A GB 722341A GB 714952 A GB714952 A GB 714952A GB 714952 A GB714952 A GB 714952A GB 722341 A GB722341 A GB 722341A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- elements
- rods
- section
- blades
- 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
722,341. Turbine blades. ROLLS-ROYCE, Ltd. March 11, 1953 [March 19, 1952], No. 7149/52. Class 110 (3). A turbine blade is formed from rod-like elements of a ceramic material disposed substantially parallel to each other and to the longitudinal axis of the blade, the elements extending throughout the length of the blade and within the blade profile. The ceramic elements may have a uniform circular, triangular or polygonal cross-section and may be bonded together by a high-temperature cement and the cement may be arranged to form a smooth surface for the blade. The ceramic elements 14 in the blades shown in Fig. 1 are of the same cross-section and form a blade of substantially solid cross-section, but the blade may be formed with a passage therethrough. In Fig. 4, the ceramic elements 17 on the convex side of the blade are of larger cross-sectional area than the remainder of the elements 18 of the blade. The elements may also be tapered along their length so as to form a blade of tapering cross-section, or they may be disposed with their axes skewed to the longitudinal axis of the blade so as to form a twisted blade. A tapered blade may also be formed by using a high-temperature cement non-uniformly between adjacent ceramic elements. The ends of the blades may be encircled by straps or collars 13 and a metal sheath 21, Fig. 4, may be disposed around the ceramic elements to form the profile surface of the blade and arranged to be substantially a non-load-transmitting portion of the blade. The blades in Fig. 1 are mounted in apertures formed in inner and outer coaxial annular members 10, 11. In one arrangement, the rods are about 0.060 in. in diameter and there are about 90 rods per blade. The rods 17 in Fig. 4 are about 0.125 in. in diameter and the rods 18 are 0.060 in. in diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB714952A GB722341A (en) | 1952-03-19 | 1952-03-19 | Improvements relating to turbine blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB714952A GB722341A (en) | 1952-03-19 | 1952-03-19 | Improvements relating to turbine blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB722341A true GB722341A (en) | 1955-01-26 |
Family
ID=9827554
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB714952A Expired GB722341A (en) | 1952-03-19 | 1952-03-19 | Improvements relating to turbine blades |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB722341A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2914300A (en) * | 1955-12-22 | 1959-11-24 | Gen Electric | Nozzle vane support for turbines |
| US2920868A (en) * | 1955-10-05 | 1960-01-12 | Westinghouse Electric Corp | Dampened blade structure |
| US3032317A (en) * | 1958-10-24 | 1962-05-01 | Robert G Frank | Jet turbine bucket wheel |
| US3572971A (en) * | 1969-09-29 | 1971-03-30 | Gen Electric | Lightweight turbo-machinery blading |
| US5221188A (en) * | 1990-12-21 | 1993-06-22 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Blade device for turbo-engines |
| EP3168142A1 (en) * | 2015-11-09 | 2017-05-17 | General Electric Company | Airfoil with energy absorbing edge guard |
-
1952
- 1952-03-19 GB GB714952A patent/GB722341A/en not_active Expired
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2920868A (en) * | 1955-10-05 | 1960-01-12 | Westinghouse Electric Corp | Dampened blade structure |
| US2914300A (en) * | 1955-12-22 | 1959-11-24 | Gen Electric | Nozzle vane support for turbines |
| US3032317A (en) * | 1958-10-24 | 1962-05-01 | Robert G Frank | Jet turbine bucket wheel |
| US3572971A (en) * | 1969-09-29 | 1971-03-30 | Gen Electric | Lightweight turbo-machinery blading |
| US5221188A (en) * | 1990-12-21 | 1993-06-22 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Blade device for turbo-engines |
| EP3168142A1 (en) * | 2015-11-09 | 2017-05-17 | General Electric Company | Airfoil with energy absorbing edge guard |
| CN107035413A (en) * | 2015-11-09 | 2017-08-11 | 通用电气公司 | Airfoil with energy absorption edge protection thing |
| CN107035413B (en) * | 2015-11-09 | 2020-05-12 | 通用电气公司 | Airfoil with energy absorbing edge guard |
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