Claims
- 1. An improved method of constructing a tubomachinery blade of the type having convex and concave side walls defining a cavity with a radially outer tip end, and a tip cap which forms a closure for the tip end comprising the steps of:
- a. forming a blade having convex and concave side walls defining a cavity with an open tip end;
- b. providing respective radially spaced platform and retaining means in said cavity on the inner periphery of the side walls, proximate the tip end thereof;
- c. providing a closure element in the cavity to interconnect the side walls near the tip end to close a portion thereof;
- d. placing a tip cap in contiguity with the radially outer surface of said closure element; and
- e. sliding said tip cap to a position wherein it is captured between said platform and said retaining means to close another portion of the tip end.
- 2. An improved method of constructing a turbomachine blade as set forth in claim 1 wherein said respective platform and retaining means for formed integrally with said side walls.
- 3. An improved method of constructing a turbomachine blade as set forth in claim 2 wherein said platform and retaining means are formed by the casting process at the same time the blade side walls are formed.
- 4. An improved method of constructing a turbomachine blade as set forth in claim 1 wherein said closure means is formed by the casting process at the same time the side walls are formed.
- 5. An improved method of constructing a turbomachine blade as set forth in claim 1 wherein the radially outer surface of said platform means and said closure means are placed in substantially the same plane.
- 6. An improved method of constructing a turbomachine blade as set forth in claim 1 wherein said closure element is placed centrally with respect to the respective leading and trailing edges of the blade.
- 7. An improved method of constructing a turbomachine blade as set forth in claim 1 and including the steps of placing a second tip cap in contiguity with the radially outer surface of said closure element; and, sliding said second tip cap to a second position where it is captured between said platform and said retaining means to close a third portion of the tip end.
- 8. An improved method of constructing a turbomachine blade as set forth in claim 1 and including the further step of brazing said tip cap to said closure element.
- 9. An improved method of constructing a turbomachine blade as set forth in claim 1 wherein the cavity includes at least one longitudinal rib for defining a coolant flow passage and further including the step of connecting the radially outer end of said rib to said tip cap as by brazing.
Parent Case Info
This is a division of application Ser. No. 609,346, filed Sept. 2, 1975, now U.S. Pat. No. 3,982,851 issued on Sept. 28, 1976, and assigned to the assignee of the present invention.
Government Interests
The invention herein described was made in the course of or under a contract, or a subcontract thereunder, with the United States Department of the Air Force.
US Referenced Citations (7)
Divisions (1)
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Number |
Date |
Country |
Parent |
609346 |
Sep 1975 |
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