TURBINE ENGINE COMPRISING A CONTRAROTATING PROPELLER RECEIVER SUPPORTED BY A STRUCTURAL CASING ATTACHED TO THE INTERMEDIATE HOUSING

• US 20130098066A1
• Filed: 10/18/2012
• Published: 04/25/2013
• Est. Priority Date: 10/21/2011
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Gallet, Francois, Grede, Audrey
• Granted Patent: US 9,217,391 B2
• Time in Patent Office: Days
• US Class Current: 60/796
• CPC Class Codes: F02K 3/062 with aft fan
• CPC Class Codes: F02K 3/072 with counter-rotating , e.g. fan rotors
• CPC Class Codes: F05D 2220/324 to drive unshrouded, low solidity propeller
• CPC Class Codes: F05D 2220/325 to drive unshrouded, high solidity propeller
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The present invention relates to an open rotor type aircraft turbine engine (1), comprising a contrarotating propeller receiver (30) and a dual-body gas generator (14) comprising a low-pressure compressor (16) and a high-pressure compressor (18) separated by an intermediate housing (27), said gas generator being arranged upstream from said receiver.

According to the invention, the turbine engine further comprises a structural casing (50) for supporting the receiver (30), surrounding the gas generator (14) and having a downstream end (50a) attached to said receiver and an upstream end (50b) attached to said intermediate housing (27). Furthermore, it comprises additional connection means (60) between said structural supporting casing and the gas generator, arranged between the upstream and downstream ends (50b, 50a) of the casing.

Claims

1. An aircraft turbine engine comprising:

a contrarotating propeller receiver and a dual-body gas generator comprising a low-pressure compressor and a high-pressure compressor separated by an intermediate housing, said gas generator being arranged upstream from said receiver,

a structural casing for supporting the receiver, said casing surrounding the gas generator and having a downstream end attached to said receiver and an upstream end attached to said intermediate housing,

connection means between said structural supporting casing and the gas generator, arranged between the upstream and downstream ends of the casing, wherein said connection means are designed to enable relative movement between said structural support casing and the gas generator.

2. The turbine engine according to claim 1, wherein said connection means comprise a plurality of connecting rods distributed circumferentially with respect to each other, about the longitudinal axis of the turbine engine.

3. The turbine engine according to claim 2, wherein said connecting rods mounted at the ends thereof with ball joints.

4. The turbine engine according to claim 1, wherein said connection means are arranged downstream from the combustion chamber of the gas generator.

5. The turbine engine according to claim 1, further comprising means for extracting an air flow at the outlet of the low-pressure compressor and routing same to an annular space defined externally by the structural support casing, the turbine engine being designed such that said air flow is introduced into a power turbine of the receiver.