# US 5,343,619 A · Hollow blade for a turbomachine and method of manufacturing said blade

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- Number: US 5,343,619 A
- Document ID: US5343619A
- Status: Granted
- Kind: A
- Application number: 08/111,892
- Filed: 1993-08-26
- Granted: 1994-09-06
- Earliest claimed: 1992-09-02
- Assignees: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
- Inventors: Alain M. J. Lardellier
- Web page: https://patentgrep.com/patent/US5343619A

## CPC

- F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)}
- Y10T 29/49336: Blade making
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A hollow blade for a turbomachine comprises a unitary body having a multiplicity of transverse cavities in at least the airfoil shaped portion of the blade, and plugs disposed within the cavities and restoring the surface continuity of the intrados and extrados faces of the aerofoil shaped portion, the plugs being rigidly secured to the unitary body, such as by welding.

## Claims

### Claim 1

A method of manufacturing a hollow blade for a turbomachine comprising the following steps:
a) producing a unitary blade blank by forging, said blade blank including an airfoil shaped portion;
b) machining a multiplicity of holes in said airfoil shaped portion such that a zone of specific width is left clear at the edge of said airfoil shaped portion and said holes are substantially evenly distributed over the remaining area of said airfoil portion and provide a cavity ratio of about 90% in said remaining area;
c) producing plugs with a shape adapted to the holes formed during step (b) and to the profile of the respective surface of said airfoil shaped portion, be it the intrados face or the extrados face;
d) placing said plugs in position in said holes formed during step (b);
e) fixing said plugs to said blade blank by high energy beam welding while said plugs are in position in said holes; and
f) finishing said blank to obtain the required aerodynamic profile.

### Claim 2 (depends on 1)

A method according to claim 1 wherein step (c) comprises producing first plug parts adapted to the shape of said holes and the profile of said intrados face of said airfoil shaped portion, producing second plug parts adapted to the shape of said holes and the profile of said extrados face, and welding said first and second plug parts together in pairs to produce said plugs.