Turbine casing comprising ring sector attachment means

Patent metadata

Field	Value
Publication number	US-10487689-B2
Application number	US-201214003490-A
Country	US
Kind code	B2
Filing date	Mar 6, 2012
Priority date	Mar 7, 2011
Publication date	Nov 26, 2019
Grant date	Nov 26, 2019

Abstract

An aircraft turbine casing configured to carry a set of ring sectors that partly delimits a conduit inside which a gas flow passes through the turbine, including a dynamic mechanism adjusting radial position of ring sectors, an upstream radial lug that connects an upstream end of each ring sector to the casing, and a downstream radial lug that connects a downstream end of each ring sector to the casing. The upstream lug is made as a single piece with the casing and is directly connected to the upstream end of each ring sector.

First claim

The invention claimed is:

1. An aircraft turbine casing configured to carry a set of ring sectors that partly delimits a conduit inside which a gas flow passes through the turbine, comprising:
a dynamic mechanism to adjust a radial position of the ring sectors by controlled injection of an air flow on portions of an annular wall of the casing;
an upstream radial lug that connects an upstream end of each ring sector, along a direction of gas flow to the casing, and a downstream radial lug that connects a downstream end of each ring sector to the casing; and
a guide conduit that is delimited by the upstream radial lug, the downstream radial lug, the annular wall and by an annular guide plate that is in contact with the upstream radial lug and downstream radial lug and is arranged radially between the annular wall and the ring sector;
wherein only the downstream end of the annular plate comprises outlet orifices globally oriented towards the ring sector,
wherein at least the upstream radial lug is made as a single piece with the casing and is directly connected to the upstream end of each ring sector, and
wherein the upstream radial lug includes air passage orifices for ventilation of the ring sectors that open up into the guide conduit.

2. The casing according to claim 1 , wherein the upstream and downstream radial lugs are made as a single piece with the casing and are directly connected to each ring sector.

3. The casing according to claim 1 , wherein each radial lug is formed from a ring extending radially inwards, in a radial plane relative to a principal axis of the turbine, starting from an inner annular face of the annular wall of the casing.

4. A turbine for an aircraft turbine machine comprising:
a stator assembly including the casing according to claim 1 ; and
a plurality of ring sectors that are directly fixed at least to the upstream radial lug of the casing.

5. An aircraft turbine machine comprising the turbine according to claim 4 .

6. The casing according to claim 1 , wherein air exits the guide conduit at a downstream end edge of the annular plate.

7. The casing according to claim 1 , wherein the annular plate includes an axially extending section and a radially extending section downstream of the axially extending section, and the downstream end is located further downstream of the radially extending section.

Assignees

• Bonneau Damien
• Cordier Jean Christophe Marc
• Garin Fabrice Marcel Noel
• Safran Aircraft Engines

Inventors

• Bonneau Damien
• Cordier Jean-Christophe Marc
• Garin Fabrice Marcel Noel

Classifications

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2240/11

  Shroud seal segments · CPC title