ROTOR FOR A GAS TURBINE ENGINE COMPRISING A ROTOR SPOOL AND A ROTOR RING

• US 20110239661A1
• Filed: 03/31/2011
• Published: 10/06/2011
• Est. Priority Date: 04/01/2010
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Weller, Lionel René Henri, BELMONTE, Olivier
• Granted Patent: US 8,757,980 B2
• Time in Patent Office: Days
• US Class Current: 60/796
• 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: 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

Abstract

A one-piece rotor spool (20) for a gas turbine engine extending along the axis of the engine, the spool comprising an upstream portion (20A) and a downstream portion (20B) that are radially offset relative to one another, the radially outer portion (20B) comprising a plurality of housings (24) for rotor blades formed in the outer surface of said radially outer portion (20B), the spool (20) being characterized in that the radially inner portion (20A) comprises attachment means (23) designed to interact with a rotor ring (30) in order to prevent a tangential movement of the rotor ring (30) relative to the radially inner portion (20A).

Claims

1. A rotor (100) for a gas turbine engine comprising a one-piece rotor spool (20) extending along the axis of the engine (X) and a rotor ring (30), the spool (20) comprising an upstream portion (20A) and a downstream portion (20B) that are radially offset relative to one another;

the radially outer portion comprising a plurality of housings (24) for rotor blades (40B) formed in the outer surface of the radially outer portion;

the rotor ring (30) comprising a plurality of housings (34) of rotor blades (40A) formed in the outer surface of the ring (30);

a rotor in which the radially inner portion of the spool comprises attachment means (23) designed to interact with attachment means (33) of the rotor ring (30), formed in the inner surface of the ring (30), in order to prevent a tangential movement of the rotor ring (30) relative to the rotor spool (20).

2. The rotor as claimed in claim 1, wherein the means for attaching the spool (20) are arranged in order to allow an axial movement of the rotor ring (30) relative to the radially inner portion.

3. The rotor as claimed in claim 1, wherein the means for attaching the spool take the form of attachment teeth (23) extending radially outward.

4. The rotor as claimed in claim 1, wherein the radially outer portion of the spool (20) corresponds to the downstream portion (20B) and the radially inner portion corresponds to the upstream portion (20A).

5. The rotor as claimed in claim 1, wherein the means for attaching the ring (30) take the form of attachment recesses (33) extending radially inward.

6. A gas turbine engine comprising a rotor (100) as claimed in claim 5.