Compressor turbojet engine whose rotor has a movable upstream stage

• US 5,473,883 A
• Filed: 11/01/1994
• Issued: 12/12/1995
• Est. Priority Date: 11/03/1993
• Status: Expired due to Term

• Current Assignee: Snecma (Safran SA)
• Original Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation
• Inventors: Naudet, Jacky S.
• Primary Examiner(s): Bertsch, Richard A.
• Assistant Examiner(s): RICHMAN, HOWARD
• Application Number:
  US08/332,784
• Time in Patent Office: 406 Days
• Field of Search: 60/39.161, 60/39.31
• US Class Current: 60/791
• CPC Class Codes: F01D 25/285 Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• CPC Class Codes: F01D 5/06 Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections F01D5/022, F01D5/023 take precedence
• CPC Class Codes: F04D 29/321 for axial flow compressors
• CPC Class Codes: F05D 2220/327 to drive shrouded, high solidity propeller
• CPC Class Codes: F05D 2230/70 Disassembly methods

Abstract

Turbojet engine compressor . . . Its rotor (43) includes a movable end portion (45), such as a monoblock vaned disk able to be removed and replaced by a block. High and low pressure shaft lines (54) are formed into several portions to enable these operations to take place without having to dismantle the entire engine.

Claims

1. A turbojet engine including a compressor composed of a rotor and a stator, the rotor being composed of a body and mobile vanes linked to the body, the stator being composed of a stator housing and fixed vanes linked to the stator housing, the fixed and mobile vanes being grouped into axially alternate stages, the turbojet engine also including a shaft line traversing the body, the body being composed of a disk at an upstream end in a flow direction of gases flowing in the engine and another portion at which the disk is assembled by a centering bearing and a fixing flange, the disk comprising a stage of mobile vanes which is most upstream on the rotor, the shaft line being composed of separable portions and assembled by linking means situated upstream of the disk, wherein the disk is a monobloc vaned disk and the stator housing is assembled with another housing forming an extension of the stator housing at a parting line of said stator housing immediately upstream of the monobloc vaned disk, and the another portion of the body is secured to one of the portions of the shaft line and the disk is linked to the shaft line only through said another portion.

2. A turbojet engine according to claim 1, wherein the compressor comprises a high pressure compressor situated downstream of a low pressure compressor and upstream of two turbines, two of the separable portions of the shaft line are concentric and bolted together with a nut, a first of the separable portions which are bolted together being integral with the rotor of the high pressure compressor, the other of the separable portions which are bolted together being integral with a second rotor which is part of the low pressure compressor.

3. A turbojet engine according to claim 2, wherein the nut is disposed in such a way as to press a bearing of said shaft line against a shoulder of said shaft line.

4. A turbojet engine according to claim 3, including a brace ring spline-fitted around the shaft line and clamped between the nut and the bearing.

5. A turbojet engine according to claim 1, wherein the other housing bears a stage of fixed vanes situated upstream of the stage of mobile vanes of the monobloc vaned disk.

6. A turbojet engine according to claim 1, wherein the monobloc vaned disk comprises balancing masses.

7. A turbojet engine according reliefs to claim 1, wherein the monobloc vaned disk comprises engagable by extracting or mounting tools.

8. A turbojet engine according to claim 1, wherein the centering bearing is circular and the fixing flange has a flat face.