US 2019/0099803 A1 · CORE FOR CASTING A BLADE OF A TURBOMACHINE

Abstract

A core for casting a blade of a turbomachine, the core comprising a first part for defining a first cavity and a second part of which at least one portion defines a second cavity located between the first cavity and the tip of the blade. The portion of the second part includes a through-hole that ends opposite the first part so as to define, in the cast blade, an outer face of a duct for removing dust from the first cavity. An alumina pin which is secured to the end face of the first part extends into the through-hole to define the inner face of the duct. A centering sheath placed between the pin and the through-hole centers the pin in relation to the through-hole. The centering sheath is made of a material that is intended to dissolve before the blade is cast around the core.

Claims10

Dependent claims

1-9. (canceled)

Core (16) for the moulding of a turbine engine blade, this blade comprising a blade extending along a spanwise direction (EV) and ending with a peak, this core (16) comprising a first core element (17) to delimit a first inner cavity of the blade and a second blade element (18) of which at least one portion (19) delimits a second inner cavity of the blade, these core elements (17, 18) being rigidly connected to each other, the second cavity being situated between the first cavity and the peak of the blade along the spanwise direction (EV), and wherein:

the portion (19) of the second core element (18) which delimits the second cavity comprises a through bore (26) oriented along the spanwise direction (EV), and which leads to the right of an end face (28) of the first core element (17) to delimit in the moulded blade, an outer face of a dust removal conduit (32) of the first cavity, this conduit (32, 38) crossing the second cavity (33) from one end to the other by leading to the peak of the blade;
an alumina rod (27) with a diameter less than the diameter of the through bore (26), and extending inside the through bore (26) by being fixed to the end face (28) of the first core element (17), to delimit the inner face of the conduit (32, 38);
centring means (29) interposed between the rod (27) and the through bore (26) to centre this rod with respect to the hole (26), these centring means (29) being made of a material intended to be dissolved before proceeding with casting the blade around said core (16).

Dependencies are inferred from the claim text.

Facts

Application

16/080,377Filed 27 Feb 2017

Priority

FR 16 517001 Mar 2016

Published

4 Apr 2019

Term ends

Not estimatedThe source records don’t support an estimate.

Classification11 codes

B22C 9/103
Cores; Manufacture or installation of cores: multipart cores
F01D 5/187
Hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades: convection cooling
F01D 5/20
Form or construction: specially-shaped blade tips to seal space between tips and stator
F05D 2230/211
By casting: by precision casting, e.g. microfusing or investment casting

Core for casting a blade of a turbomachine

Life of this patent

Core for casting a blade of a turbomachine

Life of this patent

Abstract

Claims10