A gas turbine engine with a rear mount assembly including link rods interconnecting the bypass duct wall and the core portion and connecting assemblies connected to the bypass duct wall. Each connecting assembly has inner and outer surfaces bordering an opening through which an outer end of a respec
A gas turbine engine with a rear mount assembly including link rods interconnecting the bypass duct wall and the core portion and connecting assemblies connected to the bypass duct wall. Each connecting assembly has inner and outer surfaces bordering an opening through which an outer end of a respective link rod extends. The outer surface is accessible from outside the bypass duct wall. A first locking member is engaged to the outer end in a first locked position, and includes an abutment portion located radially inwardly of the inner surface and abutting the inner surface, and an outer portion protruding radially outwardly through the opening beyond the outer surface. A second locking member is engaged the outer end in a second locked position, and has an abutment portion located radially outwardly of the outer surface and abutting the outer surface. A method of supporting a core portion is also discussed.
대표청구항▼
1. A gas turbine engine comprising: a core portion received within an annular bypass duct wall, a bypass air passage being defined by an annular space between the core portion and bypass duct wall;a front mount assembly supporting the core portion in proximity of an inlet of the bypass air passage;a
1. A gas turbine engine comprising: a core portion received within an annular bypass duct wall, a bypass air passage being defined by an annular space between the core portion and bypass duct wall;a front mount assembly supporting the core portion in proximity of an inlet of the bypass air passage;a rear mount assembly supporting the core portion in proximity of an outlet of the bypass air passage, the rear mount assembly including: a plurality of link rods interconnecting the bypass duct wall and the core portion to form a load transfer path therebetween;a plurality of connecting assemblies, each connecting assembly being connected to the bypass duct wall, each connecting assembly having: an inner surface facing radially inwardly and an outer surface located radially outwardly of the inner surface and facing radially outwardly, both the inner and outer surfaces bordering an opening through which an outer end of a respective one of the link rods extends, the outer surface being accessible from outside of the bypass duct wall,a first locking member engaged to the outer end in a first locked position, the first locking member including a first abutment portion located radially inwardly of the inner surface and abutting the inner surface, the first locking member having an outer portion protruding radially outwardly through the opening beyond the outer surface, anda second locking member engaged to the outer end in a second locked position, the second locking member having a second abutment portion located radially outwardly of the outer surface and abutting the outer surface. 2. The gas turbine engine as defined in claim 1, wherein the plurality of link rods interconnect the bypass duct wall and a mid-turbine frame of the core portion. 3. The gas turbine engine as defined in claim 1, wherein the second abutment portion is annular, the outer portion of the first locking member extending within the second abutment portion. 4. The gas turbine engine as defined in claim 1, wherein the first and second locking members are threadingly engaged to the outer end of the respective one of the link rods. 5. The gas turbine engine as defined in claim 1, wherein each of the connecting assemblies includes a bracket received in a hole defined through the bypass duct wall and connected to the bypass duct wall, the bracket having an engagement wall defining the opening through which the outer end of the respective one of the link rods extends, the engagement wall being compressed between the first and second abutment portions. 6. The gas turbine engine as defined in claim 5, wherein the engagement wall defines the inner surface, the outer surface being defined by a locking washer received radially outwardly of and against the engagement wall, the locking washer engaging the outer portion of the first locking member. 7. The gas turbine engine as defined in claim 5, wherein the bracket and the outer end of the respective one of the link rods include complementary anti-rotation features in engagement with one another. 8. The gas turbine engine as defined in claim 5, wherein the engagement wall is a first engagement wall and the opening is a first opening, the bracket having a second engagement wall having a different orientation than that of the first engagement wall, the second engagement wall having a second opening defined therethrough, an outer end of another one of the link rods extending through the second opening, the connecting assembly further comprising: a third locking member engaged to the outer end of the other one of the link rods in a third locked position, the third locking member including a third abutment portion located radially inwardly of the second engagement wall, the third locking member having an outer portion protruding radially outwardly through the second opening beyond the second engagement wall; anda fourth locking member engaged to the outer end of the other one of the link rods in a fourth locked position, the fourth locking member having a fourth abutment portion located radially outwardly of the second engagement wall;wherein the second engagement wall is compressed between the third and fourth abutment portions. 9. The gas turbine engine as defined in claim 8, wherein the first and second engagement walls are interconnected between the first and second openings, the first and second openings being aligned along an axial direction of the engine and being circumferentially spaced apart. 10. A rear mount assembly for a gas turbine engine, the assembly comprising: a plurality of connecting assemblies each including a bracket sized to be received in a respective one of a plurality of holes defined through a bypass duct wall of the gas turbine engine, each bracket including an engagement wall having an opening defined therethrough;for each bracket, a first link rod having an outer end received through the opening, the first link rod extending radially inwardly from the bracket; andeach of the connecting assemblies including: a first locking member engaged to the outer end of the first link rod, the first locking member having a first abutment portion located radially inwardly of the engagement wall, the first abutment portion abutting an inner surface of the connecting assembly to prevent a radially outward movement of the outer end, the first locking member having an outer portion protruding radially outwardly of the engagement wall through the opening; anda second locking member engaged to the outer end, the second locking member having a second abutment portion located radially outwardly of the engagement wall, the second abutment portion abutting an outer surface of the connecting assembly to prevent a radially inward movement of the outer end. 11. The assembly as defined in claim 10, wherein the inner surface is defined by the engagement wall, the first abutment portion abutting the inner surface. 12. The assembly as defined in claim 10, wherein the outer surface is defined by a locking washer received radially outwardly of and against the engagement wall, the locking washer engaging the outer portion of the first locking member. 13. The assembly as defined in claim 10, wherein the first and second locking members are threadingly engaged to the outer end of the first link rod. 14. The assembly as defined in claim 10, wherein the second abutment portion is annular, the outer portion of the first locking member extending within the second abutment portion. 15. The assembly as defined in claim 10, wherein opening is a first opening, the bracket further including a locking wall located radially inwardly of the engagement wall, the locking wall having a second opening defined therethrough in alignment with the first opening, the outer end of the first link rod extending through the second opening, and wherein the bracket and the outer end include complementary anti-rotation features in engagement with one another, the anti-rotation features of the bracket being defined in the locking wall around the second opening. 16. The assembly as defined in claim 10, wherein the engagement wall is a first engagement wall, the opening is a first opening, the inner surface is a first inner surface, and the outer surface is a first outer surface, each of the brackets including a second engagement wall having a second opening defined therethrough, the assembly further comprising: for each of the brackets, a second link rod having an outer end received through the second opening, the second link rod extending radially inwardly from the bracket with a different orientation than the first link rod; andfor each second link rod: a third locking member engaged to the outer end of the second link rod, the third locking member having a third abutment portion located radially inwardly of the second engagement wall, the third abutment portion abutting a second inner surface of the connecting assembly to prevent a radially outward movement of the outer end of the second link rod, the third locking member having an outer portion protruding radially outwardly of the second engagement wall through the second opening; anda fourth locking member engaged to the outer end of the second link rod, the fourth locking member having a fourth abutment portion located radially outwardly of the second engagement wall, the fourth abutment portion abutting a second outer surface of the connecting assembly to prevent a radially inward movement of the outer end of the second link rod. 17. The assembly as defined in claim 16, wherein the first and second engagement walls are interconnected between the first and second openings. 18. A method of supporting a core portion within a bypass duct wall of a gas turbine engine, the method comprising: engaging an inner end of each of a plurality of link rods to the core portion and engaging a first locking member to an outer end of each of the link rods;inserting the outer end of each of the link rods through a respective opening of a connecting assembly of the bypass duct wall from inside of the bypass duct wall, the first locking member having an abutment portion larger than the respective opening and an outer portion protruding radially outwardly from the respective opening;from outside of the bypass duct wall, manipulating each first locking member by the outer portion to adjust a position of each first locking member until the abutment portion of each first locking member abuts an inner surface of the connecting assembly defined around the respective opening and the core portion has a desired position within the bypass duct wall, and locking the position of the first locking member; andfrom outside of the bypass duct wall, engaging a second locking member to the outer end of each of the link rods and moving each second locking member radially inwardly until each second locking member abuts an outer surface of the connecting assembly defined around the respective opening, and locking a position of the second locking member. 19. The method as defined in claim 18, wherein adjusting the position of each first locking member includes moving the first locking member along a threaded engagement between the first locking member and the outer end of a respective one of the link rods, and moving each second locking member includes moving the second locking member along a threaded engagement between the second locking member and the outer end. 20. The method as defined in claim 19, wherein locking the position of the first locking member includes engaging a locking washer to the first locking member, the outer surface abutting the second locking member being defined by the locking washer.
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이 특허에 인용된 특허 (17)
Sandy, David F; Zheng, Zhijun, Adjustable engine mount.
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