# US 8,464,425 B2 · Process for manufacturing a single-piece blisk with a temporary blade support ring removed before a milling step

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- Number: US 8,464,425 B2
- Document ID: US8464425B2
- Status: Granted
- Kind: B2
- Application number: 12/933,978
- Filed: 2009-03-25
- Published: 2011-02-03
- Granted: 2013-06-18
- Earliest claimed: 2008-03-31
- Assignees: Snecma
- Applicants: Serge Berlanger; Sebastien Bordu; Thierry Jean Maleville; Christophe Charles Maurice Roca
- Inventors: Serge Berlanger; Sebastien Bordu; Thierry Jean Maleville; Christophe Charles Maurice Roca
- Web page: https://patentgrep.com/patent/US8464425B2

## CPC

- B23P 13/02: in which only the machining operations are important
- B23C 3/18: for shaping screw-propellers, turbine blades, or impellers
- B23P 15/006: {turbine wheels}
- B24C 1/045: {for cutting (energy dissipating devices therefor B26F3/008)}
- F01D 5/34: Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)}
- F05D 2230/10: by removing material
- Y10T 29/4932: Turbomachine making
- Y10T 29/49325: Shaping integrally bladed rotor
- Y10T 29/49336: Blade making
- Y10T 29/49799: Providing transitory integral holding or handling portion
- B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q)
- B23C: MILLING (broaching B23D; broach-milling in making gears B23F; arrangement for copying or controlling B23Q)
- B24C: ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- 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
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A process for manufacturing a single-piece bladed disk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material forming a connecting mechanism between at least two directly consecutive blade preforms, the connecting mechanism being at a radial spacing from the disk; then removing the connecting mechanism; then milling the blade preforms.

## Claims

### Claim 1

A process for manufacturing a single-piece bladed blisk, comprising:
using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material to form a connecting mechanism between at least two directly consecutive blade preforms, the connecting mechanism being at a radial spacing from the disk;
removing the connecting mechanism; and
milling the blade preforms.

### Claim 2 (depends on 1)

The process according to claim 1, wherein the cutting using an abrasive water jet is done such that the connecting mechanism joins more than three blade preforms to each other, or directly consecutive to each other.

### Claim 3 (depends on 2)

The process according to claim 2, wherein the cutting using an abrasive water jet is done such that the connecting mechanism approximately forms a ring.

### Claim 4 (depends on 3)

The process according to claim 3, wherein the cutting using an abrasive water jet is made such that the ring connects all blade preforms to each other.

### Claim 5 (depends on 3)

The process according to claim 3, wherein the cutting using an abrasive water jet is done so that the ring connects tips of the blade preforms to each other.

### Claim 6 (depends on 1)

The process according to claim 1, wherein the milling the blade preforms is done so as to obtain profiled blade blanks, followed by a milling to finish blade blanks, so as to obtain blades to a final profile.

### Claim 7 (depends on 1)

The process according to claim 1, wherein the diameter of the single-piece blisk is greater than or equal to 800 mm.

### Claim 8 (depends on 1)

The process according to claim 1, wherein the thickness of the single-piece blisk is greater than or equal to 100 mm.

### Claim 9 (depends on 1)

The process according to claim 1, wherein the blades of the single-piece blisk are twisted.

### Claim 10 (depends on 1)

The process according to claim 1, wherein the material block used is made of titanium or a titanium alloy.

### Claim 11 (depends on 1)

The process according to claim 1, wherein the single-piece blisk is a single-piece blisk for an aircraft turbine engine.

### Claim 12 (depends on 1)

The process according to claim 1, wherein the single-piece blisk is a single-piece blisk for a turbine or compressor rotor in an aircraft turbine engine.