초록

A split disk assembly for a gas turbine engine includes a forward disk section and an aft disk section, the aft disk section engageable with the forward disk section to retain a multitude of rotor blades therebetween.

대표청구항 ▼

1. A split disk assembly for a gas turbine engine comprising: a forward disk section; andan aft disk section engageable with said forward disk section to retain a multitude of rotor blades therebetween. 2. The assembly as recited in claim 1, wherein said forward disk section is defined by a forward

1. A split disk assembly for a gas turbine engine comprising: a forward disk section; andan aft disk section engageable with said forward disk section to retain a multitude of rotor blades therebetween. 2. The assembly as recited in claim 1, wherein said forward disk section is defined by a forward rotor hub. 3. The assembly as recited in claim 1, wherein said aft disk section is defined by an aft rotor hub. 4. The assembly as recited in claim 1, wherein said forward disk section defines a forward rim and said aft disk section defines an aft rim, said forward rim and said aft rim circumferentially constant. 5. The assembly as recited in claim 1, wherein said forward disk section defines a forward rim and said aft disk section defines an aft rim, said forward rim and said aft rim do not include a blade load slot. 6. The assembly as recited in claim 1, wherein said forward disk section and said aft disk section are mountable upon a tie-shaft that generates a compressive load to at least partially retain said forward disk section to said aft disk section. 7. The assembly as recited in claim 1, wherein one of said forward disk section and said aft disk section includes a hub, a rim and a web which extends between said hub and said rim. 8. The assembly as recited in claim 1, wherein said engine stage is a high pressure compressor stage. 9. A split disk assembly for a gas turbine engine comprising: a forward disk section which at least partially defines an engine stage; andan aft disk section which at least partially defines another engine stage, said aft disk section engageable with said forward disk section to retain a multitude of rotor blades therebetween. 10. The assembly as recited in claim 9, wherein said forward disk section defines a forward rim and said aft disk section defines an aft rim, said forward rim and said aft rim do not include a blade load slot. 11. The assembly as recited in claim 9, wherein said engine stage is an 8th stage. 12. The assembly as recited in claim 9, wherein one of said aft rim and said forward rim extends to a hub via a web. 13. The assembly as recited in claim 9, wherein said engine stage is a high pressure compressor stage. 14. The assembly as recited in claim 11, wherein said hub section is defined by a forward rotor hub. 15. The assembly as recited in claim 14, wherein said disk section and said forward hub at least partially defines a 1st compressor stage. 16. The assembly as recited in claim 11, wherein said hub section is defined by an aft rotor hub. 17. The assembly as recited in claim 16, wherein said disk section and said aft rotor hub at least partially defines an 8th compressor stage. 18. A split disk assembly for a gas turbine engine comprising: a disk section; anda hub section engageable with said disk section to retain a multitude of rotor blades therebetween. 19. The assembly as recited in claim 18, wherein said disk section includes a hub, a rim and a web which extends between said hub and said rim. 20. The assembly as recited in claim 18, wherein said engine stage is a high pressure compressor stage.