# US 10,864,660 B2 · Core for the moulding of a blade having superimposed cavities and including a de-dusting hole traversing a cavity from end to end

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- Number: US 10,864,660 B2
- Document ID: US10864660B2
- Status: Granted
- Kind: B2
- Application number: 15/195,088
- Filed: 2016-06-28
- Published: 2016-12-29
- Granted: 2020-12-15
- Earliest claimed: 2015-06-29
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Matthieu Jean Luc Vollebregt; Patrick Emilien Paul Emile Huchin
- Web page: https://patentgrep.com/patent/US10864660B2

## CPC

- B29C 33/76: Cores (B29C33/02 - B29C33/70, {B29C41/40, B29C53/74, B29C53/82} take precedence)
- B22C 9/103: {Multipart cores}
- F01D 5/187: {Convection cooling}
- F01D 5/20: Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)}
- F05D 2230/21: by casting
- F05D 2260/607: Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00)
- B22C: FOUNDRY MOULDING (moulding refractory materials in general B28B)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A core for the moulding of a turbine engine blade, this blade including a vane extending along a spanwise direction and ending in a top, this core including a first core element to delimit a first internal cavity and a second core element of which at least one portion delimits a second internal cavity. The second cavity is situated between the first cavity and the top of the blade along the spanwise direction, and the portion of the second core element delimiting the second cavity includes a through hole, which emerges in line with an end face of the first core element to constitute a de-dusting conduit of the first cavity, this conduit traversing the second cavity from end to end while emerging in the top of the blade.

## Claims

### Claim 1

A core for the moulding of a turbine engine blade, said turbine engine blade including a vane extending along a spanwise direction of the blade and ending in a top, said core including: a first core element to delimit a first internal cavity of the blade and a second core element of which at least one portion delimits a second internal cavity of the blade, these core elements being rigidly connected together, the second cavity being situated between the first cavity and the top of the blade along the spanwise direction,
wherein the portion of the second core element which delimits the second cavity includes a through hole having a general orientation corresponding to that of the spanwise direction, wherein said through hole emerges in line with an end face of the first core element to form in the moulded blade a bridge fitting traversing the second cavity, and
a rod having a diameter smaller than that of the through hole by an amount sufficient that an annular space, into which annular space can flow material of the turbine engine blade during a process of moulding of the turbine engine blade, may be formed between an outer periphery of the rod and the portion of the second core element defining the through hole, the rod traversing the through hole and implanted in the end face of the first core element for providing a de-dusting conduit of the first cavity, said de-dusting conduit traversing the second cavity from end to end while emerging in the top of the blade and being isolated from the second cavity by the material of the turbine engine blade which has flowed into said annular space during the process of moulding of the turbine engine blade.

### Claim 2 (depends on 1)

The core according to claim 1, in which the through hole is situated in a central region of the portion of the second core element which delimits the second cavity, to be spaced apart from each lateral face of said second core element, such that the bridge fitting comprises an obstacle dividing air circulating in the second cavity of the finished blade into two lateral flows.

### Claim 3 (depends on 1)

The core according to claim 1, in which the first core element is arranged to delimit a cooling channel of a trailing edge of the blade, and in which the second core element is arranged to delimit a beneath bath cavity of the blade.

### Claim 4 (depends on 1)

The core according to claim 1, wherein the rod is an alumina rod.