Intermediate casing extension of improved design

Patent metadata

Field	Value
Publication number	US-9920654-B2
Application number	US-201314652573-A
Country	US
Kind code	B2
Filing date	Dec 16, 2013
Priority date	Dec 18, 2012
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

Abstract

The invention relates to an extension ( 30 ) of an intermediate frame for an aircraft turbine engine, that will project downstream from an outer ring of the intermediate frame, this extension comprising a downstream annular connecting part ( 64 ) preferably forming an annular groove ( 66 ) open radially outwards, into which the nacelle cowls will fit ( 38 ), the end ( 64 ) comprising at least one first angular sector ( 76 b ). According to the invention, the extension comprises a body ( 77 ) made from a single piece comprising a junction ring ( 74 ) and at least one second angular sector ( 76 a ) of said downstream annular connecting part ( 64 ), the first angular sector being added onto the extension body ( 77 ).

First claim

What is claimed is:

1. Extension ( 30 ) of an intermediate frame ( 21 ) for an aircraft turbine engine, that will project downstream from an outer ring ( 23 ) of said intermediate frame, said extension comprising a downstream annular connecting part ( 64 ) forming retention means ( 66 ) designed to hold nacelle cowls ( 38 ), said downstream annular connecting part ( 64 ) comprising at least a first angular sector ( 76 b ),
wherein said extension comprises a body ( 77 ) made from a single piece comprising a junction ring ( 74 ) and an integrally formed at least one second angular sector ( 76 a ) of said downstream annular connecting part ( 64 ), said first angular sector ( 76 b ) being added onto said extension body ( 77 ), and in that the extension comprises a plurality of first angular sectors ( 76 b ) and a plurality of second angular sectors ( 76 a ), a sum of all second angular sectors ( 76 a ) covering at least 80% of the circumference of the body.

2. Extension according to claim 1 , wherein the first angular sectors ( 76 b ) are mounted onto the body by bolts ( 77 ), in recesses ( 79 ) formed between two second directly consecutive sectors ( 76 a ) of said body.

3. Extension according to claim 1 , wherein said first angular sectors ( 76 b ) are made from a first material, and the second angular sectors ( 76 a ) are made from a second material different from the first material.

4. Extension according to claim 1 , wherein said retention means are formed from a groove ( 66 ) open radially outwards, into which the nacelle cowls ( 38 ) will fit.

5. Extension according to claim 1 , wherein said retention means are formed from a retention flange ( 66 ) projecting radially outwards.

6. Turbine engine ( 2 ) for an aircraft, comprising an intermediate frame ( 21 ) fitted at the downstream end of its outer ring ( 23 ) with an extension ( 30 ) according to claim 1 .

7. Turbine engine according to claim 6 , wherein the junction ring ( 74 ) of the body ( 77 ) is fitted with an annular collar ( 75 ) fastening the body to the downstream end of the outer ring ( 23 ) of the intermediate frame ( 21 ).

8. Propulsion assembly ( 1 ) for an aircraft comprising a turbine engine ( 2 ) according to claim 6 , and a nacelle ( 32 ) comprising the nacelle cowls ( 38 ) cooperating with said retention means ( 66 ).

9. Propulsion assembly ( 1 ) according to claim 8 , further comprising a turbine engine EMS ( 4 ) comprising a rigid structure ( 11 ) and means of fastening the turbine engine on said rigid structure, said nacelle cowls ( 38 ) thus being articulated on said rigid structure ( 11 ).

10. Extension according to claim 3 , wherein the first material is titanium or one of its alloys.

11. Extension according to claim 3 , wherein the second material is aluminium or one of its alloys.

12. Extension according to claim 5 , wherein said retention flange holds the nacelle cowls ( 38 ) by means of a retaining structure ( 93 ) clamping the retention flange ( 66 ) and a portion ( 68 ) of said nacelle cowls.

Assignees

• Snecma

Inventors

• Dubois Margaux Justine Emma
• Demoulin Alexandre Christophe Adrien

Classifications

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F01D25/24 Primary

  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 title

• B64D27/00

  Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F02K3/06

  with front fan · CPC title