Gas turbine engine comprising a composite component and a metal component which are connected by a flexible fixing device
View Patent ↗A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.
1. A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and comprising:
a composite part;
a metal part; and
a fixing device for flexible fixing of the metal part and the composite part to one another, the fixing device comprising:
a flexible connecting element comprising a first fixing portion connected to the metal part by a first axial connection and a second fixing portion connected to the composite part by a second axial connection, the flexible connecting element comprising an axially extending free end; and
a rigid locking element comprising a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the rigid locking element being aligned radially with the free end of the flexible connecting element, the free end of the rigid locking element forming abutment means of the free end of the flexible connecting element in event of radial deformation of the flexible connecting element while the engine is in operation,
wherein the first fixing portion of the flexible connecting element and the second fixing portion of the flexible connecting element are axially offset, and the free end of the flexible connecting element is located axially between the first fixing portion of the flexible connecting element and the second fixing portion of the flexible connecting element.
2. An engine according to claim 1 , wherein the free end of the rigid locking element is radially outside the free end of the flexible connecting element.
3. An engine according to claim 1 , wherein the flexible connecting element comprises an intermediate portion connecting the first fixing portion to the second fixing portion, the intermediate portion comprising through-holes to give flexibility to the flexible connecting element.
4. An engine according to claim 3 , wherein the intermediate portion of the flexible connecting element extends axially.
5. An engine according to claim 1 , wherein the fixing device comprises a sealing element mounted between the flexible connecting element and the rigid locking element.
6. An engine according to claim 5 , wherein the sealing element is in a form of a curved metal sheet.
7. An engine according to claim 1 , wherein the flexible connecting element and the rigid locking element are connected to the metal part by a same axial connection.
8. An engine according to claim 1 , wherein a radially inner portion of the fixing device is thicker by comparison with a radially outer portion of the fixing device to be able to retain any debris from the engine.
9. An engine according to claim 1 , wherein the rigid locking element is thicker than the flexible connecting element.
10. An engine according to claim 1 , wherein the free end of the flexible connecting element is thicker than the first and second fixing portions of the flexible connecting element.
11. An engine according to claim 1 , wherein the metal part is a turbine housing of a turbojet engine and the composite part is an exhaust case of the turbojet engine.
12. An engine according to claim 1 , wherein the first fixing portion of the flexible connecting element is upstream of the second fixing portion of the flexible connecting element, and the free end of the flexible connecting element is downstream of the first fixing portion of the flexible connecting element and is upstream of the second fixing portion of the flexible connecting element.
13. A gas turbine engine for propulsion of an aircraft, said engine extending axially from upstream to downstream and comprising:
a composite part;
a metal part; and
a fixing device for flexible fixing of said metal part and said composite part to one another, said fixing device comprising:
a flexible connecting element comprising a first fixing portion connected to the metal part by a first axial connection and a second fixing portion connected to the composite part by a second axial connection, said flexible connecting element comprising an axially extending free end; and
a rigid locking element comprising a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the flexible connecting element, the free end of the rigid locking element forming abutment means of the free end of the flexible connecting element in the event of radial deformation of the connecting element while the engine is in operation,
wherein the free end of the rigid locking element is radially outside the free end of the flexible connecting element.