Structural support bracket for gas flow path

1. A structural support system for a can annular gas turbine engine having an arrangement for delivering gases from a plurality of combustors to a first row of turbine blades, the arrangement comprising an integrated exit piece (IEP) for each combustor, the IEPs being joined together to form an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering a gas flow to the first row of blades, the structural support system for the arrangement comprising:

an inner support structure located axially forward from the arrangement;

a bracket structure having a forward end connected to the inner support structure and having a rearward end connected to a radially inner side of a respective IEP of the plurality of IEPs, the bracket structure including:

an axial bracket member having a first end located at the rearward end of the bracket structure and a second end axially aligned with the inner support structure, and the second end being located in circumferentially spaced relation to the inner support structure; and

a transverse bracket member having a first end connected to the second end of the axial bracket member and having a second end circumferentially spaced from the first end of the transverse bracket member and forming the forward end of the bracket structure attached to the inner support structure.

2. The structural support system of claim 1 , wherein the axial and transverse bracket members are formed by respective plates having respective radial inner and outer edges.

3. The structural support system of claim 2 , wherein a plane is defined by the plate forming the transverse bracket member and the plane of the transverse bracket member extends generally perpendicular to a plane defined by the plate forming the axial bracket member.

4. The structural support system of claim 2 , wherein the first end of the axial bracket member includes inner and outer attachment locations at respective inner and outer edges of the axial bracket member that are rigidly attached to the respective IEP.

5. The structural support system of claim 4 , wherein the respective IEP includes an inlet chamber for receiving gases from a respective combustor of the plurality of combustors and further includes a connection segment for connection to an outlet end of an upstream adjacent respective IEP, the connection segment including a radially inner wall and a radially outer wall, and the inner and outer attachment locations of the axial bracket member being connected to the respective inner and outer walls.

6. The structural support system of claim 5 , wherein the connection segment of the respective IEP is located radially inward from the inlet chamber.

7. The structural support system of claim 5 , wherein the connection segment of the respective IEP has a generally rectangular cross section and a flange extends outwardly from the inner and outer walls, and the inner and outer attachment locations of the axial bracket member are attached to the flange.

8. The structural support system of claim 2 , wherein the transverse bracket member includes two circumferentially spaced attachment locations where the transverse bracket member is rigidly attached to the inner support structure, and the plate forming the transverse bracket member is rigid in the radial direction and is flexible in the axial direction.

9. The structural support system of claim 1 , wherein the inner support structure is formed by a shaft cover of the gas turbine engine.

10. The structural support system of claim 1 , including an outer support structure formed by a turbine vane carrier, and a structural attachment member extending between and attaching a radially outer side of the respective IEP to the outer support structure.

11. A structural support system for a can annular gas turbine engine having an arrangement for delivering gases from a plurality of combustors to a first row of turbine blades, the arrangement comprising an integrated exit piece (IEP) for each combustor, the IEPs being joined together to form an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering a gas flow to the first row of blades, the structural support system for the arrangement comprising:

an inner support structure located axially forward from the arrangement;

a bracket structure having a forward end connected to the inner support structure and having a rearward end connected to a radially inner side of a respective IEP of the plurality of IEPs, the bracket structure including:

an axial bracket member having a first end located at the rearward end of the bracket structure and a second end axially aligned with the inner support structure, and the second end being located in spaced relation to the inner support structure; and

a transverse bracket member having a first end connected to the second end of the axial bracket member and having a second end located in spaced relation to the first end of the transverse bracket member and forming the forward end of the bracket structure attached to the inner support structure, wherein the transverse bracket member is flexible in the axial direction and is relatively rigid in the radial direction.

12. The structural support system of claim 11 , wherein the axial and transverse bracket members are formed by respective plates, each of the plates being elongated along a major dimension and having shorter minor dimension, and the plates being joined at a joint that extends in the direction of the minor dimension of each of the plates.

13. The structural support system of claim 12 , wherein a plane is defined by the plate forming the transverse bracket member and the plane of the transverse bracket member extends generally perpendicular to a plane defined by the plate forming the axial bracket member.

14. The structural support system of claim 12 , wherein the first end of the axial bracket member includes inner and outer attachment locations at respective inner and outer edges of the axial bracket member that are rigidly attached to the respective IEP.

15. The structural support system of claim 14 , wherein the respective IEP includes an inlet chamber for receiving gases from a respective combustor of the plurality of combustors and further includes a connection segment for connection to an outlet end of an upstream adjacent respective IEP, the connection segment including a flange having a radially inner portion and a radially outer portion, and the inner and outer attachment locations of the axial bracket member being connected to the respective inner and outer portions of the flange.

16. The structural support system of claim 15 , wherein the connection segment of the respective IEP is located radially inward from the inlet chamber.

17. The structural support system of claim 15 , wherein the connection segment of the respective IEP has a generally rectangular cross section and a flange extends outwardly from the inner and outer walls, and the inner and outer attachment locations of the axial bracket member are attached to the flange.

18. The structural support system of claim 12 , wherein the transverse bracket member includes circumferentially spaced attachment locations where the plate forming the transverse bracket member is rigidly attached to the inner support structure.

19. The structural support system of claim 11 , wherein the inner support structure is formed by a shaft cover of the gas turbine engine.

20. The structural support system of claim 11 , including an outer support structure formed by a turbine vane carrier, and a structural attachment member extending between and attaching a radially outer side of the respective IEP to the outer support structure.