The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein a primary gas channel for axial gas flow is defined between the e
The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein a primary gas channel for axial gas flow is defined between the elements (22), wherein the component (27) has an inlet side for gas entrance and an outlet side for gas outflow, and an annular load transfer structure (23) positioned internally of the inner ring (20) for transferring loads between said elements (22) and a bearing structure (24) for a turbine shaft (11) positioned centrally in the component (27), wherein the annular load transfer structure (23) extends circumferentially along at least a part of an inner side of the inner ring (20) and inwards in a radial direction of the component (27), wherein the annular load transfer structure (23) has a first portion (23a) and a second portion (23b), and wherein the first portion (23a) is located closer to the inner ring (20) than the second portion (23b). The invention is characterized in that the first portion (23a) is radially inclined between a first position (30) in the vicinity of the inner ring (20) and an axially displaced second position (31) and wherein the second portion (23b) extends from the second position (31) and is inclined in relation to the first portion (23a), and wherein the annular load transfer structure (23) is provided with a plurality of circumferentially spaced load carrying members (32) arranged at a side of the first portion (23a) axially facing in a direction towards the second position (31), wherein the load carrying members (32) are arranged to form a load carrying connection between the annular load transfer structure (23) and said elements (22) via the inner ring (20). The invention also concerns a gas turbine engine (1) comprising a component (27) of the above type.
대표청구항▼
1. A gas turbine engine component, comprising: an outer ring;an inner ring; anda plurality of circumferentially spaced elements extending between the inner ring and the outer ring, wherein a primary gas channel for axial gas flow is defined between the elements,wherein the component has an inlet sid
1. A gas turbine engine component, comprising: an outer ring;an inner ring; anda plurality of circumferentially spaced elements extending between the inner ring and the outer ring, wherein a primary gas channel for axial gas flow is defined between the elements,wherein the component has an inlet side for gas entrance and an outlet side for gas outflow, and an annular load transfer structure positioned internally with respect to the inner ring for transferring loads between said elements, and a bearing structure for a turbine shaft positioned centrally in the component,wherein:the annular load transfer structure extends circumferentially along at least a part of an inner side of the inner ring and inwards in a radial direction of the component, wherein the annular load transfer structure has a first portion and a second portion, and wherein the first portion is located closer to the inner ring than the second portion,the first portion is radially inclined between a first position in the vicinity of the inner ring and an axially displaced second position, and the second portion extends from the second position and is inclined in relation to the first portion,the annular load transfer structure is provided with a plurality of circumferentially spaced load carrying members arranged at a side of the first portion axially facing in a direction towards the second position, further wherein the load carrying members are arranged to form a load carrying connection between the bearing structure and said elements via the inner ring,the load carrying members are arranged in a set of pairs, wherein each of said set of pairs are positioned radially inwards of a corresponding element located on an opposite, outer side of the inner ring such that a load can be transferred in a substantially straight radial direction between a certain pair of load carrying members and an element corresponding to said pair, andthe two load carrying members in the pairs are inclined towards each other such that the distance between the two load carrying members increases in a radial direction towards a center point of the component. 2. A gas turbine engine component according to claim 1, wherein each load carrying member extends in a radial direction along the side of the first portion, and each load carrying member extends also in an axial direction along the inner side of the inner ring. 3. A gas turbine engine component according to claim 1, wherein: each of the load carrying members has a plate-like shape,a first edge side of the load carrying member extends along the side of the first portion,another edge side of the load carrying member extends in an axial direction along the inner side of the inner ring. 4. A gas turbine engine component according to claim 1, wherein each load carrying member is positioned radially inwards of a corresponding element located on an opposite, outer side of the inner ring such that a load can be transferred in a substantially straight radial direction between a certain load carrying member and its corresponding element. 5. A gas turbine engine component according to claim 4, wherein an axial extension of the load carrying member along the inner ring substantially corresponds to at least a part of an axial extension of the corresponding element along the opposite side of the inner ring. 6. A gas turbine engine component according to claim 1, wherein an axial extension of the load carrying members in each of the pairs along the inner ring substantially corresponds to an axial extension of a first and second side, respectively, of the corresponding element along the opposite side of the inner ring. 7. A gas turbine engine component according to claim 1, wherein the load carrying members extend along the first portion from the first position to the second position. 8. A gas turbine engine component according to claim 1, wherein the second position is located axially downstream of the first position. 9. A gas turbine engine component according to claim 8, wherein the second portion is radially inclined from the axially downstream position towards the inlet side of the component. 10. A gas turbine engine component according to claim 1, wherein the load carrying members form an integral part of the annular load transfer structure. 11. A gas turbine engine component according to claim 1, wherein the shaft bearing structure is positioned in an axial position forwards of the element in a primary gas flow direction through the component and that the second portion is inclined towards the bearing structure. 12. A gas turbine engine component according to claim 1, wherein a point of connection between the first and second portions in said second position is substantially closer to the inner ring than to the bearing structure. 13. A gas turbine engine component according to claim 1, wherein the first portion extends from a position in the vicinity of a leading edge of the element to said second position. 14. A gas turbine engine comprising a component, wherein the component comprises: an outer ring;an inner ring; anda plurality of circumferentially spaced elements extending between the inner ring and the outer ring, wherein a primary gas channel for axial gas flow is defined between the elements,wherein the component has an inlet side for gas entrance and an outlet side for gas outflow, and an annular load transfer structure positioned internally with respect to the inner ring for transferring loads between said elements, and a bearing structure for a turbine shaft positioned centrally in the component,wherein:the annular load transfer structure extends circumferentially along at least a part of an inner side of the inner ring and inwards in a radial direction of the component, wherein the annular load transfer structure has a first portion and a second portion, and wherein the first portion is located closer to the inner ring than the second portion,the first portion is radially inclined between a first position in the vicinity of the inner ring and an axially displaced second position, and the second portion extends from the second position and is inclined in relation to the first portion,the annular load transfer structure is provided with a plurality of circumferentially spaced load carrying members arranged at a side of the first portion axially facing in a direction towards the second position, further wherein the load carrying members are arranged to form a load carrying connection between the bearing structure and said elements via the inner ring,the load carrying members are arranged in a set of pairs, wherein each of said set of pairs are positioned radially inwards of a corresponding element located on an opposite, outer side of the inner ring such that a load can be transferred in a substantially straight radial direction between a certain pair of load carrying members and an element corresponding to said pair, andthe two load carrying members in the pairs are inclined towards each other such that the distance between the two load carrying members increases in a radial direction towards a center point of the component.
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이 특허에 인용된 특허 (6)
Somanath, Nagendra; Kumar, Keshava B.; Sowa, William A., Embedded mount for mid-turbine frame.
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