Device for supporting a turbine ring, turbine having such a device, and turbine engine having such a turbine

• US 8,932,009 B2
• Filed: 09/02/2010
• Issued: 01/13/2015
• Est. Priority Date: 09/04/2009
• Status: Active Grant

• Current Assignee: Safran Helicopter Engines
• Original Assignee: Turbomeca
• Inventors: Moraines, Christophe-Olivier, Pardo, Frederic Philippe Jean-Jacques
• Primary Examiner(s): Nguyen, Ninh H
• Application Number:
  US13/393,934
• Publication Number:
  US 20120163957A1
• Time in Patent Office: 1,594 Days
• Field of Search: 415/173.1, 415/116, 415/213.1
• US Class Current: 415/173.1
• CPC Class Codes: F01D 11/24 by selectively cooling-heating stator or rotor components
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A device for supporting a ring of a gas turbine, the ring configured to surround mobile blades of the turbine which are driven by a gas stream flowing upstream to downstream. The device includes at least one upstream hook facing upstream, to be housed in an upstream groove of the ring, opened toward the downstream direction, and at least one downstream hook facing downstream, to be housed in a downstream groove of the ring, opened toward the upstream direction. The hooks are protected and clearances at apexes of the blades are more easily controlled. The device further includes, upstream from the upstream hook, a mechanism injecting cooling gas to cool the upstream hook and/or includes, downstream from the downstream hook, a mechanism injecting a cooling gas to cool the downstream hook.

Claims

1. A supporting device for a ring of a gas turbine, the ring configured to enclose moving blades of the turbine driven by a gas flow flowing from upstream to downstream, the device comprising:

at least one upstream hook, facing upstream, configured to be accommodated in an upstream groove of the ring, which groove is open in the downstream direction;

at least one downstream hook, facing downstream, configured to be accommodated in a downstream groove of the ring, which groove is open in the upstream direction;

a pressurized cavity formed between the upstream hook and downstream hook, the pressurized cavity being supplied with cooling gases; and

at least one of means for injecting cooling gases for cooling the upstream hook positioned upstream of the upstream hook, and means for injecting cooling gases for cooling the downstream hook downstream of the downstream hook;

arranged so that this injection is done without going through the pressurized cavity.

2. An aggregate constituted by a device as claimed in claim 1, and a turbine ring, the turbine ring comprising:

an upstream groove, which groove is open in the downstream direction, and an downstream groove, which groove is open in the upstream direction, in which at least one of the upstream groove of the ring includes a curvilinear surface for contact with the upstream hook and the downstream groove of the ring includes a curvilinear surface for contact with the downstream hook.

3. An aggregate as claimed in claim 2, further comprising at least one of at least one upstream seal arranged to ensure gas-tightness between the ring and the upstream hook, the upstream seal being accommodated in the upstream groove of the ring, and/or at least one downstream seal arranged to ensure gas-tightness between the ring and the downstream hook, the downstream seal being accommodated in the downstream groove of the ring.

4. An aggregate as claimed in claim 2, further comprising an upstream supporting part comprising the upstream hook and a downstream supporting part comprising the downstream hook, in which the upstream supporting part and downstream supporting part are in one piece and the ring is sectorized into at least two ring sectors.

5. An aggregate as claimed in claim 4, in which the upstream supporting part and downstream supporting part are arranged to be mounted with the ring by sliding the supporting parts one on the other and by shrink fitting.

6. An aggregate as claimed in claim 2, further comprising an upstream supporting part comprising the upstream hook and a downstream supporting part comprising the downstream hook, in which the ring is in one piece, the downstream supporting part is in one piece, and the upstream supporting part is sectorized into at least two upstream supporting part sectors.

7. A turbine comprising a supporting device in accordance with the device of claim 1.

8. A turboshaft engine comprising a turbine in accordance with the turbine of claim 7.