A turbine engine rotor assembly includes a turbine engine rotor disk that extends axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface. The rotor disk includes one or more blade retention slots arranged circumferentially around the centerli
A turbine engine rotor assembly includes a turbine engine rotor disk that extends axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface. The rotor disk includes one or more blade retention slots arranged circumferentially around the centerline. A first of the blade retention slots extends axially into the rotor disk from a disk end surface at the first disk end to a slot end surface, and radially into the rotor disk from the outer disk surface to a slot base surface.
대표청구항▼
1. A turbine engine rotor assembly, comprising: a monolithic turbine engine rotor disk extending axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface, the rotor disk comprising one or more blade retention slots arranged circumferentially ar
1. A turbine engine rotor assembly, comprising: a monolithic turbine engine rotor disk extending axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface, the rotor disk comprising one or more blade retention slots arranged circumferentially around the centerline;wherein a first of the blade retention slots extends axially partially into the rotor disk from a disk end surface at the first disk end to a slot end surface of the rotor disk, and radially into the rotor disk from the outer disk surface to a slot base surface. 2. The rotor assembly of claim 1, wherein the first of the blade retention slots comprises a neck portion and a root portion adapted to mate with a blade root of a rotor blade;the neck portion extends radially from the outer disk surface to the root portion, and comprises a lateral first slot width; andthe root portion extends radially from the neck portion to the slot base surface, and comprises a lateral second slot width that is greater than the first slot width. 3. The rotor assembly of claim 2, wherein the rotor disk further comprises an aperture that extends radially from the outer disk surface to the root portion, and that extends laterally from the neck portion to an aperture side surface. 4. The rotor assembly of claim 3, wherein the aperture is a first aperture;the rotor disk further comprises a second aperture that extends radially from the outer disk surface to the root portion, and that extends laterally from the neck portion to a second aperture side surface; andthe first of the blade retention slots extends laterally between the first aperture and the second aperture. 5. The rotor assembly of claim 4, wherein the aperture side surface is a first aperture side surface, a lateral aperture width is defined between the first aperture side surface and the second aperture side surface, and the aperture width is greater than or substantially equal to the second slot width. 6. The rotor assembly of claim 3, wherein the aperture is axially located proximate the slot end surface. 7. The rotor assembly of claim 3, wherein the aperture comprises a circular segment cross-sectional geometry. 8. The rotor assembly of claim 1, wherein the first disk end comprises a forward disk end, and the second disk end comprises an aft disk end. 9. The rotor assembly of claim 1, further comprising one or more rotor blades arranged circumferentially around the centerline, wherein a first of the rotor blades comprises a blade root that is mated with the first of the blade retention slots. 10. The rotor assembly of claim 9, wherein the rotor disk is configured as a fan rotor disk, and the rotor blades are configured as fan blades. 11. The rotor assembly of claim 9, wherein the rotor disk is configured as a compressor rotor disk, and the rotor blades are configured as compressor blades. 12. The rotor assembly of claim 9, wherein the rotor disk is configured as a turbine rotor disk, and the rotor blades are configured as turbine blades. 13. The rotor assembly of claim 9, wherein the rotor disk further comprises an axial blade retention element connected to the first disk end adjacent to the disk end surface. 14. A method for manufacturing a turbine engine rotor disk comprising one or more blade retention slots, the rotor disk extending axially along a centerline between a first disk end and a second disk end and radially to an outer disk surface, the blade retention slots arranged circumferentially around the centerline, the method comprising: machining a first slot into the rotor disk with at least a first rotating cutting tool, the first slot extending axially from a disk end surface at the first disk end partially into the rotor disk to a first slot end surface which forms an end of the first slot, and radially from the outer disk surface to a first slot base surface; andmachining one or more surfaces of the first slot with at least a second rotating cutting tool to provide a first of the blade retention slots. 15. The method of claim 14, wherein the first of the blade retention slots comprises a neck portion and a root portion;the neck portion extends radially from the outer disk surface to the root portion, and comprises a lateral first slot width; andthe root portion extends radially from the neck portion to a slot base surface, and comprises a lateral second slot width that is greater than the first slot width. 16. The method of claim 15, further comprising machining an aperture into the rotor disk with a third rotating cutting tool, wherein the aperture extends radially from the outer disk surface to the root portion, and extends laterally from the neck portion to an aperture side surface. 17. The method of claim 16, wherein the aperture comprises a first aperture, and further comprising machining a second aperture into the rotor disk with the third rotating cutting tool concurrently to the machining of the first aperture, wherein the second aperture extends radially from the outer disk surface to the root portion, and extends laterally from the neck portion to a second aperture side surface, and wherein the first slot extends laterally between the first aperture and the second aperture. 18. The method of claim 16, wherein the second rotating cutting tool enters the first slot at the first disk end and exits the first slot through the aperture during the machining of the one or more surfaces of the first slot. 19. The method of claim 16, wherein the second rotating cutting tool enters the first slot through the aperture and exits the first slot at the first disk end during the machining of the one or more surfaces of the first slot. 20. A method for manufacturing a turbine engine rotor disk comprising one or more blade retention slots, the rotor disk extending axially along a centerline between a first disk end and a second disk end and radially to an outer disk surface, the blade retention slots arranged circumferentially around the centerline, the method comprising: machining a first slot into the rotor disk with at least a first rotating cutting tool, the first slot extending axially from a disk end surface at the first disk end to a first slot end surface, and radially from the outer disk surface to a first slot base surface; andmachining one or more surfaces of the first slot with at least a second rotating cutting tool to provide a first of the blade retention slots;wherein the first rotating cutting tool begins and finishes the machining of the first slot at the first disk end, and the second rotating cutting tool enters and exits the first slot at the first disk end during the machining of the one or more surfaces of the first slot.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (12)
Pepperman Michael Barton, Apparatus and method for locking blades into a rotor.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.