Nozzle ring with adhesive bonded blading for aircraft engine compressor
View Patent ↗Blades ( 3 ) extending radially from the inner shroud ( 1 ) to the outer shroud ( 2 ) are attached to the inner shroud by means of a sealing cement containing an organic polyimide-based polymer adhesive.
1. A compressor nozzle ring for an aircraft engine including 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 blade passing through a corresponding aperture formed in the inner shroud and being attached to the inner shroud with a sealing cement containing an organic polymer adhesive, wherein said adhesive is polyimide based,
wherein an insert disposed inside the inner shroud and in proximity to the inner shroud delineates in conjunction with the inner shroud and the blades a space that is filled with said cement, and
wherein said insert takes the form of a flexible sheet.
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 end regions of the blades project radially inward beyond the inner shroud.
4. The nozzle ring according to claim 1 , wherein the flexible sheet forms pockets at the blade ends, said pockets extending radially away from the inner shroud.
5. The nozzle ring according to claim 1 , 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 1 , wherein the flexible sheet is a glass fibre or carbon fibre fabric impregnated with polyimide.
7. The nozzle ring according to claim 1 , wherein said cement is in film form.
8. The nozzle ring according to claim 1 , wherein said cement is in the form of foam.
9. 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.
10. The nozzle ring according to claim 1 , wherein the blades are attached to the outer shroud by electron beam welding.
11. A compressor comprising the compressor nozzle ring of claim 1 .
12. An engine comprising the compressor of claim 11 .