# US 10,479,514 B2 · Assembly for turbine machine with open rotor contra-rotating propellers, comprising a small duct for the passage of ancillaries

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- Number: US 10,479,514 B2
- Document ID: US10479514B2
- Status: Granted
- Kind: B2
- Application number: 15/398,445
- Filed: 2017-01-04
- Published: 2017-07-06
- Granted: 2019-11-19
- Earliest claimed: 2016-01-05
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Clementine Charlotte Marie Mouton; Olivier Belmonte; Jeremy Phorla Lao; Didier Jean-Louis Yvon
- Web page: https://patentgrep.com/patent/US10479514B2

## CPC

- B64D 27/10: of gas-turbine type (jet aircraft B64D27/16)
- B64C 11/306: {specially adapted for contrarotating propellers}
- B64C 11/38: fluid, e.g. hydraulic
- B64C 11/48: Units of two or more coaxial propellers
- F01D 7/00: Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30)
- F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)}
- F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16)
- F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H)
- F02K 3/025: {the by-pass flow being at least partly used to create an independent thrust component}
- F02K 3/072: with counter-rotating {, e.g. fan} rotors
- B64D 2027/005: {Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]}
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2220/325: to drive unshrouded, high solidity propeller
- F05D 2230/60: Assembly methods
- F05D 2240/90: Mounting on supporting structures or systems
- F05D 2260/40311: of the epicyclical, planetary or differential type
- F05D 2260/79: Bearing, support or actuation arrangements therefor
- F05D 2270/64: Hydraulic actuators
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64C: AEROPLANES; HELICOPTERS
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- 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

An assembly for an aircraft turbine machine including a receiver for a pair of open rotor contra-rotating propellers, the assembly including a duct, ancillaries routed inside the duct, an attachment case, attachment device of the duct on an annular installation portion of the case. The attachment device in an assembled configuration include a split ring fitted with internal projections housed inside orifices in the duct; a radial loading surface of the ring made on the portion the surface being tapered and narrowing along a first axial direction, and being in contact with a peripheral surface of the complementary shaped tapered split ring; device of axially loading the ring along the first direction, the device being blocked in the axial direction on the portion.

## Claims

### Claim 1

An assembly for an aircraft turbine machine comprising a receiver for a pair of open rotor contra-rotating propellers, the assembly comprising a duct, ancillaries routed inside the duct, and an attachment case comprising an annular installation portion on which a first end of the duct is fixed by attachment means, the annular installation portion of the attachment case being arranged around the first end of the duct,
wherein the attachment means in an assembled configuration include:
a split ring fitted with internal projections housed inside corresponding orifices formed through said first end of the duct;
a radial loading surface of the split ring made on the annular installation portion of the attachment case, the radial loading surface being tapered and narrowing along a first axial direction of the duct, and being in contact with a complementary tapered peripheral surface of the split ring;
axial loading means of axially loading the split ring along said first direction, said axial loading means being blocked in the axial direction on the annular installation portion of the attachment case.

### Claim 2 (depends on 1)

The assembly according to claim 1, wherein in the assembled configuration, the internal projections are stopped in the radial and axial directions in the orifices of said first end of the duct.

### Claim 3 (depends on 1)

The assembly according to claim 1, wherein said axial loading means include a nut with an axial bearing surface and an internal thread cooperating with an external thread formed on the annular installation portion of the attachment case.

### Claim 4 (depends on 3)

The assembly according to claim 3, wherein a closing plug at the first end of the duct, said plug including an external rim gripped in the axial direction between the split ring and the axial bearing surface of the nut.

### Claim 5 (depends on 1)

The assembly according to claim 1, wherein the number of internal projections is between two and ten, each having an annular extent of between 10 and 40°.

### Claim 6 (depends on 1)

The assembly according to claim 1, wherein the cross-section of the internal projections reduces when moving radially inwards.

### Claim 7 (depends on 1)

The assembly according to claim 1, wherein the ancillaries are oil ancillaries.

### Claim 8 (depends on 1)

Turbine A turbine machine for an aircraft comprising a receiver for a pair of open rotor contra-rotating propellers, a gas generator and a reduction gear placed between the receiver and the gas generator preferably located downstream from the receiver, the turbine machine also including an assembly according to claim 1, with a duct passing through the reduction gear.

### Claim 9 (depends on 8)

The turbine machine according to claim 8, further comprising a pitch variation device for the blades of at least one of the contra-rotating propellers, said pitch variation device including a hydraulic actuator supplied by at least one ancillary routed inside the assembly duct, said duct having a second end opposite the first end fixed on a fixed part of the actuator.

### Claim 10 (depends on 1)

An installation method for an assembly according to claim 1, comprising the following steps:
put the split ring into position axially facing the annular installation portion of the attachment case, and apply load to this split ring along the circumferential direction so as to increase its diameter;
axial displacement of the duct through the annular installation portion of the attachment case and through the split ring, such that the orifices at the first end of the duct are axially facing the internal projections in the split ring;
release the circumferential load on the ring, such that its internal projections penetrate into the corresponding orifices at the first end of the duct;
relative axial displacement between the annular installation portion of the attachment case and the duct fitted with the split ring, such that the tapered radial loading surface provided on the annular installation portion comes into contact with the peripheral surface with a complementary tapered shape;
installation of the axial loading means of the split ring, this installation possibly increasing contraction of the split ring contract in the hoop direction, due to cooperation between the tapered radial loading surface and the complementary tapered peripheral surface.