Nozzle ring adhesive bonded blading for aircraft engine compressor

1. A compressor nozzle ring for an aircraft engine, said nozzle ring comprising:

an inner shroud;

an outer shroud; and

a multiplicity of blades arranged circumferentially and extending radially from the inner shroud to the outer shroud, each of the blades passing through a corresponding aperture formed in the inner shroud and being attached to the inner shroud with sealing cement containing an organic polymer adhesive,

wherein said adhesive is polyimide based;

wherein end regions of the blades project radially inward beyond the inner shroud;

wherein an insert disposed inside the inner shroud and in proximity to the inner shroud surrounds, in conjunction with the inner shroud and the blades, a continuous space along the inside of the inner shroud that is filled with said cement, and the continuous space filled with the cement continues without a gap between adjacent blades of the blades and around the end regions of the adjacent blades; and

wherein said insert surrounds the end regions of the adjacent blades including a radially innermost area of the adjacent blades.

2. The nozzle ring according to claim 1 , wherein the inner shroud and/or the blades are made of titanium.

3. The nozzle ring according to claim 1 , wherein said insert is a flexible sheet.

4. The nozzle ring according to claim 3 , wherein the flexible sheet forms pockets at the end regions of the adjacent blades, said pockets extending radially away from the inner shroud.

5. The nozzle ring according to claim 4 , wherein the flexible sheet is formed from several elements connected together in the circumferential direction of the inner shroud with partial overlap.

6. The nozzle ring according to claim 4 , wherein the flexible sheet is a glass fibre or carbon fibre fabric impregnated with polyimide.

7. A compressor nozzle ring for an aircraft engine, comprising:

an inner shroud;

an outer shroud; and

a multiplicity of blades arranged circumferentially and extending radially from the inner shroud to the outer shroud, each of the blades passing through a corresponding aperture formed in the inner shroud and being attached to the inner shroud with sealing cement containing an organic polymer adhesive,

wherein said adhesive is polyimide based;

wherein end regions of the blades project radially inward beyond the inner shroud;

wherein an insert disposed inside the inner shroud and in proximity to the inner shroud surrounds, in conjunction with the inner shroud and the blades, a space that is filled with said cement, and the space filled with the cement continues without a gap between adjacent blades of the blades;

wherein said insert includes a multiplicity of rigid parts; and

wherein each of said rigid parts is interposed between the end regions of the adjacent blades such that each individual part of said rigid parts covers a side of the end regions of each of the adjacent blades to surround the space that is filled with cement.

8. The nozzle ring according to claim 7 , wherein each of said rigid parts is force fitted between said end regions.

9. The nozzle ring according to claim 7 , wherein each of said rigid parts extends over a length of arc greater than a circumferential pitch of the adjacent blades.

10. The nozzle ring according to claim 9 , wherein said rigid parts have apertures to receive the end regions of the adjacent blades.

11. The nozzle ring according to claim 7 , wherein said rigid parts are fixed to the inner shroud by said cement.

12. The nozzle ring according to claim 7 , wherein said rigid parts are made of aluminum alloy or magnesium alloy.

13. The nozzle ring according to claim 1 , wherein said cement is in film form.

14. The nozzle ring according to claim 1 , wherein said cement is in foam form.

15. The nozzle ring according to claim 1 , wherein said polyimide-based adhesive is capable of withstanding a temperature of approximately 300° C. without deterioration during operation of the nozzle ring.

16. The nozzle ring according to claim 1 , wherein the blades are attached to the outer shroud by electron beam welding.

17. The nozzle ring according to claim 7 , wherein said insert has an angled U profile.

18. The nozzle ring according to claim 7 , wherein said insert is a non-hollow solid insert.

19. The nozzle ring according to claim 1 , wherein the insert includes a plurality of insert pieces and each of the plurality of insert pieces surrounds the end regions including the radially innermost area of a plurality of the blades.