Patent US3286927A successfully refreshed from Google Patents.
US4434835A
Expired / Lapsed
US
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Method of making a blade aerofoil for a gas turbine engine
Assignee: Rolls Royce PLC
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Filing: 1982-03-09
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Granted: 1984-03-06
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Expires: 2002-03-09
Abstract
Abstract A method of making at least the aerofoil of a blade for a gas turbine engine in which the cooling air exit passages, whether at the trailing edge or in other parts of the aerofoil, are cast rather than machined subsequently. In the method a disposable piece is formed with holes of the shape of the holes eventually required in the blade aerofoil. The piece is placed in a die and used to define part of the ceramic core required in the casting process, the die being arranged to produce a channel portion interconnecting the otherwise free ends of the parts of the core which will form the passages. The ceramic core thus formed in a lost-wax casting process to form the blade aerofoil, the channel portion being embedded in the shell mould to support the parts which define the passages.
Inventors
- 👤 Kenneth Willgoose
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 15:55
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/28; F01D5/284; B; B22; B22C; B22C9/00; B22C9/02; B22C9/04; B22C9/10; B23; B23P; B23P15/00; B23P15/04; F01D5/14; F01D5/18; F01D5/182
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
259 words
A method of making a blade aerofoil for a gas turbine engine, the aerofoil having cooling air exit passages therein, including the steps of forming a disposable piece having holes therein of the same form as the exit passages, locating the disposable piece in a die having a first internal cavity portion of the shape of the cavity within the blade aerofoil with which the passages will communicate, a second cavity portion in which fits the disposable piece, and a third cavity portion providing a channel interconnecting the free ends of the holes in the disposable piece, injecting ceramic slurry to fill the three cavity portions, hardening or allowing the ceramic to harden, separating the parts of the die, removing the ceramic core thus formed from the die, removing the disposable piece from the ceramic, placing the ceramic core thus formed in a further multi-part die having a main cavity whose form is substantially that of the external surface of the blade aerofoil and a secondary cavity within which the ceramic form from said channel portions fits, injecting wax to fill the main cavity within the die, allowing the wax to solidify, removing the wax pattern thus formed from the die, forming a shell of ceramic on the outer surface of the pattern, the ceramic shell engaging with the channel portion of the ceramic core, removing the wax from the ceramic shell, pouring molten metal into the shell mould thus formed, allowing the metal to solidify and removing the ceramic mould and the core from the cast blade aerofoil.
Claim 2
Independent Claim
259 words
A method of making a blade aerofoil for a gas turbine engine, the aerofoil having cooling air exit passages therein, including the steps of forming a disposable piece having holes therein of the same form as the exit passages, locating the disposable piece in a die having a first internal cavity portion of the shape of the cavity within the blade aerofoil with which the passages will communicate, a second cavity portion in which fits the disposable piece, and a third cavity portion providing a channel interconnecting the free ends of the holes in the disposable piece, injecting ceramic slurry to fill the three cavity portions, hardening or allowing the ceramic to harden, separating the parts of the die, removing the ceramic core thus formed from the die, removing the disposable piece from the ceramic, placing the ceramic core thus formed in a further multi-part die having a main cavity whose form is substantially that of the external surface of the blade aerofoil and a secondary cavity within which the ceramic form from said channel portions fits, injecting wax to fill the main cavity within the die, allowing the wax to solidify, removing the wax pattern thus formed from the die, forming a shell of ceramic on the outer surface of the pattern, the ceramic shell engaging with the channel portion of the ceramic core, removing the wax from the ceramic shell, pouring molten metal into the shell mould thus formed, allowing the metal to solidify and removing the ceramic mould and the core from the cast blade aerofoil.
Claim 3
Dependent Claim
27 words
A method as claimed in claim 1 and in which the step of forming the disposable piece is carried out by injection moulding in a multi-piece die.
Claim 4
Dependent Claim
41 words
A method as claimed in claim 2 and in which said holes are formed by pins extending across the die cavity from each of said parts, the pins from one part abutting at their ends the pins from the outer part.
Claim 5
Dependent Claim
14 words
A method as claimed in claim 3 and in which said pins are straight.
Claim 6
Dependent Claim
23 words
A method as claimed in claim 1 and in which the material of the disposable piece is chosen to be disposable by heating.
Claim 7
Dependent Claim
23 words
A method as claimed in claim 1 and in which the material of the disposable piece is chosen to be disposable by dissolution.
Claim 8
Dependent Claim
24 words
A method as claimed in claim 1 and in which the material of the disposable piece is chosen to be disposable by chemical attack.
References Cited (Backward Citations)
US4384607A
Cited
GB2017550A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-03-06 | 1987-09-05 | 1988-03-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-03-06 | 1991-09-05 | 1992-03-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-03-06 | 1995-09-05 | 1996-03-06 | $7700.00 | Window Closed / Lapsed |