초록 ▼

A bearing support structure is provided for installation in a gas turbine engine between radially inner first and second bearings adapted to rotatably support a first and a second rotor, respectively, and a radially outer engine frame. The support structure includes a first annular plate-shaped part

A bearing support structure is provided for installation in a gas turbine engine between radially inner first and second bearings adapted to rotatably support a first and a second rotor, respectively, and a radially outer engine frame. The support structure includes a first annular plate-shaped part and an arrangement for supporting the first bearing at one end thereof and a second annular plate-shaped part and an arrangement for supporting the second bearing at one end thereof. The first and second plate-shaped parts are joined together forming a one-piece unit for installation in the gas turbine engine.

대표청구항 ▼

The invention claimed is: 1. A bearing support structure for installation in a gas turbine engine between radially inner first and second hearings adapted to rotatably support a first and a second rotor, respectively, and radially outer engine frame, the support structure comprising a first annular

The invention claimed is: 1. A bearing support structure for installation in a gas turbine engine between radially inner first and second hearings adapted to rotatably support a first and a second rotor, respectively, and radially outer engine frame, the support structure comprising a first annular plate-shaped part and means for supporting the first bearing at one end thereof and a second annular plate-shaped part and means for supporting the second bearing at one end thereof, wherein the first and second plate-shaped arts are joined together forming a on-peice unit for installation in the gas turbine engine, and the structure comprises a third annular plate-shaped part with means for connection to the engine frame and an annular central member, the first, second, and third plate-shaped parts being fixedly joined to the annular central member. 2. A hearing support structure according to claim 1, wherein the first annular plate-shaped part and the second annular plate-shaped part extend in different directions from a joining point. 3. A bearing support structure according to claim 1, wherein the structure comprises an annular central member and the first and second plate-shaped parts are fixedly joined to the annular central member. 4. A bearing support structure according to claim 3, wherein the annular central member comprises an opening facing between the first and second annular plate-shaped parts and forming a lead-through to an opposite side of the annular central member. 5. A bearing support structure according to claim 1, wherein the second plate-shaped part and the third plate-shaped part extend with substantially a same inclination in relation to a beating support structure central axis. 6. A bearing support structure according to claim 5, wherein the structure comprises a fourth annular plate-shaped part with means for connection to the engine frame. 7. A bearing support structure according to claim 6, wherein the first and second plate-shaped parts are fixedly joined to the annular central member, and wherein the fourth plate-shaped part is fixedly joined to the annular central member. 8. A bearing support structure according to claim 6, wherein the second plate-shaped pan and the third plate-shaped part extend with substantially a same inclination in relation to a bearing support structure central axis. 9. A bearing support structure according to claim 6, wherein the third annular plate-shaped part and the fourth annular plate-shaped part extend in different directions. 10. A bearing support structure according to claim 1, wherein the bearing support structure has the general shape of an X in a cross section and the first and second plate-shaped parts each form one leg in the X. 11. A bearing support structure according to claim 1, wherein at least one of the annular plate-shaped pans has a conical shape. 12. A gas turbine engine comprising a first and a second rotor, a first and a second bearing rotatably supporting the first and second rotor, respectively, an engine frame and a bearing support structure arranged radially, between the bearings and the engine frame, the bearing support structure comprising a first annular elate-shaped part and means for supporting the first bearing at one end thereof and a second annular plate-shaped part and means for supporting the second bearing at one end thereof, wherein the first and second plate-shaped parts are joined together forming a one piece unit in the gas turbine engine, wherein the bearing support structure comprises a third annular plate-shaped part with means for connection to the engine frame and an annular central member, the first, second and third plate-shaped parts are being fixedly joined to the annular central member. 13. A gas turbine engine according to claim 12, wherein the first annular plate-shaped part and the second annular plate-shaped part extend in different directions from a joining region. 14. A gas turbine engine according to claim 12, wherein the annular central member comprises an opening facing between first and second annular plate shaped parts and forming a lead-through to an opposite side of the annular central member. 15. A gas turbine engine according to claim 12, wherein the structure comprises a fourth annular plate-shaped part with means for connection to the engine frame. 16. A gas turbine engine according to claim 15, wherein the fourth plate-shaped part is fixedly joined to the annular central member. 17. A gas turbine engine according to claim 15, wherein the third annular plate-shaped part and the fourth annular plate-shaped part extend in different directions. 18. A gas turbine engine according to claim 17, wherein at least one of the annular plate-shaped parts has a conical shape. 19. A gas turbine engine according to claim 12, wherein the bearing support structure is connected to an engine aft frame located between a high pressure turbine and a low pressure turbine. 20. A gas turbine engine according to claim 19, wherein a rearwardly located turbine frame aft mount is rigidly fastened to the engine frame.