GB734157A - Improvements in or relating to ceramic rotor blades for axial flow turbines, compressor and pumps - Google Patents
Improvements in or relating to ceramic rotor blades for axial flow turbines, compressor and pumpsInfo
- Publication number
- GB734157A GB734157A GB23168/53A GB2316853A GB734157A GB 734157 A GB734157 A GB 734157A GB 23168/53 A GB23168/53 A GB 23168/53A GB 2316853 A GB2316853 A GB 2316853A GB 734157 A GB734157 A GB 734157A
- Authority
- GB
- United Kingdom
- Prior art keywords
- compressor
- layer
- ceramic
- pumps
- relating
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
734,157. Turbine blades. MASCHINENFABRIK AUGSBURG-NURNBERG AKT.- GES. Aug. 21, 1953 [Sept. 4, 1952], No. 23168/53. Class 110 (3). In a ceramic rotor blade for an axial-flow gas turbine, compressor or pump, the supporting surfaces 3 on the blade root are each coated with a foamy, porous protective layer 5. The layer 5, which consists of a glaze or other ceramic mass, is applied before the ceramic blade is fired and may be applied, as by scattering or brushing, over an initial layer of compact glaze. Local compressive stresses occurring at the surfaces 3 cause crushing of the edges of the pores of the layer 5, resulting in a closer and more extensive fit with the corresponding surface of the rotor disc. Specification 664,986 is referred to.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE734157X | 1952-09-04 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB734157A true GB734157A (en) | 1955-07-27 |
Family
ID=6641422
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB23168/53A Expired GB734157A (en) | 1952-09-04 | 1953-08-21 | Improvements in or relating to ceramic rotor blades for axial flow turbines, compressor and pumps |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB734157A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3752600A (en) * | 1971-12-09 | 1973-08-14 | United Aircraft Corp | Root pads for composite blades |
-
1953
- 1953-08-21 GB GB23168/53A patent/GB734157A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3752600A (en) * | 1971-12-09 | 1973-08-14 | United Aircraft Corp | Root pads for composite blades |
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