V-shaped gearbox for driving turbomachine equipment

• US 10,054,001 B2
• Filed: 02/25/2014
• Issued: 08/21/2018
• Est. Priority Date: 03/14/2013
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Beutin, Bruno Albert, Ancuta, Carmen, Demoulin, Lambert Olivier Marie
• Primary Examiner(s): Kraft, Logan
• Assistant Examiner(s): Davis, Jason
• Application Number:
  US14/775,292
• Publication Number:
  US 20160032755A1
• Time in Patent Office: 1,638 Days
• Field of Search: None
• CPC Class Codes: F01D 15/12 Combinations with mechanical gearing driven by multiple engines F01D13/00
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F05D 2220/30 in turbines
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2250/38 angled, e.g. sweep angle
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: F16H 57/025 Support of gearboxes, e.g. torque arms, or attachment to other devices
• CPC Class Codes: F16H 57/03 characterised by means for reinforcing gearboxes, e.g. ribs

Abstract

A gearbox for driving equipment of a turbomachine, including a substantially V-shaped box having two arms joined together by a joining part, the arms containing gear trains joined together at the joining part, and an attachment to the turbomachine. The attachment include a mechanism for insetting and/or for attaching the joining part and a suspension device of the arms.

Claims

1. A turbine engine comprising:

a gearbox comprising a substantially V-shaped casing including two arms which are interconnected by a joining part which extends over part of a length of the arms, the arms being formed by two parts of said V-shaped casing which are separate outside said joining part, the arms containing gear lines which are located in non-parallel planes and are interconnected in a region of the joining part;

an upstream attachment system which attaches the joining part to an intermediate casing of the turbine engine; and

a downstream attachment system which attaches the arms to a casing of a high pressure compressor of the turbine engine,

wherein the gearbox is mounted downstream of a fan of the turbine engine in a space located between the casing of the high pressure compressor and an inner cylindrical wall of the intermediate casing, the arms extending downstream of the joining part along a longitudinal axis of the turbine engine and symmetrically on either side of a plane passing through the longitudinal axis of the turbine engine, and

wherein the upstream attachment system includes a tubular member with a first end connected to the V-shaped casing of the gearbox and a second end which is inserted into a cup disposed on the intermediate casing, and an outer flange provided on the second end of the tubular member which is placed on a radially outer end of the cup.

2. The turbine engine according to claim 1, wherein the arms of the V-shaped casing are interconnected by a transverse reinforcing member.

3. The turbine engine according to claim 2, wherein the downstream attachment system includes a connecting rod for each arm, and wherein the transverse reinforcing member and the connecting rods are located substantially in a same plane.

4. The turbine engine according to claim 1, wherein the downstream attachment system includes a connecting rod for each arm, and wherein the connecting rods are oriented tangentially relative to the casing of the high pressure compressor.

5. The turbine engine according to claim 1, wherein the downstream attachment system includes a connecting rod for each arm, and wherein the connecting rods are articulated to a radially outer annular flange of the casing of the high pressure compressor.

6. The turbine engine according to claim 1, wherein the downstream attachment system includes two connecting rods, each connecting rod including a first end connected to one of the arms of the V-shaped casing of the gearbox and a second end connected to a yoke attached to the casing of the high pressure compressor.

7. The turbine engine according to claim 6, wherein each connecting rod comprises means for adjusting a length thereof.