Apparatus and method for securing a rotor blade in a rotor of a turbine-type machine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/30
F01D-005/00
출원번호
US-0413753
(2006-04-28)
등록번호
US-7306433
(2007-12-11)
우선권정보
DE-10 2005 003 511(2005-01-26)
발명자
/ 주소
Klingels,Hermann
Rued,Klaus Peter
출원인 / 주소
MTU Aero Engines GmbH
대리인 / 주소
Crowell & Moring LLP
인용정보
피인용 횟수 :
5인용 특허 :
1
초록▼
A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades, or rotor blade segments, or an integrally blad
A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades, or rotor blade segments, or an integrally bladed, circumferentially closed rotor blade ring. The rotor blades, or rotor blade segments, or rotor blade ring are/is anchored in the groove extending in the circumferential direction of the rotor base body by a blade base or ring base. The groove has a profiled groove wall leg on only one side, with the blade base of the rotor blades or the rotor blade segments, or ring base of the rotor blade ring, being in contact with the profiled groove wall leg with a correspondingly profiled supporting flank.
대표청구항▼
What is claimed is: 1. A rotor of a turbine-type machine, in particular a gas turbine rotor, having a rotor base body, wherein the rotor base body has a groove extending in a circumferential direction of the rotor base body, and having an integrally bladed, circumferentially closed rotor blade ring
What is claimed is: 1. A rotor of a turbine-type machine, in particular a gas turbine rotor, having a rotor base body, wherein the rotor base body has a groove extending in a circumferential direction of the rotor base body, and having an integrally bladed, circumferentially closed rotor blade ring, wherein the rotor blade ring is anchored by a ring base in the groove of the rotor base body, wherein the groove has a profiled groove wall leg on only one side and wherein a profiled supporting flank of the ring base of the rotor blade ring is in contact with the groove wall leg, and wherein the groove and/or the rotor base body has at least one threading opening for a projection of the ring base on at least one diameter. 2. The rotor according to claim 1, wherein a width of the ring base corresponds approximately to a width of a platform of the rotor blade ring in the circumferential direction. 3. The rotor according to claim 1, wherein the ring base of the rotor blade ring has at least one projection on at least two different diameters, with the projections securing the ring base in the groove in a form-fitting manner. 4. The rotor according to claim 3, wherein the projections positioned on different diameters are arranged in approximately a same circumferential position. 5. The rotor according to claim 3, wherein at least one securing element cooperates with the projections on the ring base, wherein the securing element or each securing element secures the rotor blade ring in the groove in a circumferential position. 6. The rotor according to claim 5, wherein the securing element or each securing element has multiple recesses wherein the projections on the ring base that are positioned on an outside radially engage in the recesses in the securing element to provide a form-fitting means of securing the circumferential position of the rotor blade ring. 7. The rotor according to claim 5, wherein the securing element or each securing element is attached to the rotor base body. 8. The rotor according to claim 1, wherein the ring base has at least one projection extending radially inward on two different diameters, wherein the projections secure the rotor blade ring in the groove in an axial position and against tilting. 9. The rotor according to claim 1, wherein the groove and/or the rotor base body has at least one threading opening for a projection of the ring base on two different diameters. 10. The rotor according to claim 9, wherein the threading openings which are positioned at different diameters are arranged approximately in a same circumferential position. 11. The rotor according to claim 1, wherein the threading opening or each threading opening is integrated into a rib and/or a portion of the rotor base body which is exposed to a relatively low tension level during operation. 12. The rotor according to claim 1, wherein the supporting flank is profiled like a pine tree on only one side facing the profiled groove wall leg of the groove. 13. A gas turbine, in particular an aircraft jet engine, having at least one rotor according to claim 1. 14. A rotor of a turbine-type machine, in particular a gas turbine rotor, having a rotor base body, wherein the rotor base body has a groove extending in a circumferential direction of the rotor base body, and having an integrally bladed, circumferentially closed rotor blade ring, wherein the rotor blade ring is anchored by a ring base in the groove of the rotor base body, wherein the groove has a profiled groove wall leg on only one side and wherein a profiled supporting flank of the ring base of the rotor blade ring is in contact with the groove wall leg; wherein the ring base of the rotor blade ring has at least one projection on at least two different diameters, with the projections securing the ring base in the groove in a form-fitting manner; and wherein the projections partially overlap and/or engage a corresponding rib of the rotor base body. 15. A rotor of a turbine-type machine, comprising: a rotor base body, wherein a groove is defined between a profiled wall leg of the rotor base body and an unprofiled rib of the rotor base body and wherein the groove extends in a circumferential direction of the rotor base body; and an integrally bladed and circumferentially closed rotor blade ring having a ring base, wherein the ring base includes a profiled supporting flank; wherein the ring base is secured in the groove with the profiled wall leg of the rotor base body contacting the profiled supporting flank of the ring base and wherein the groove and/or the rotor base body has at least one threading opening for a projection of the ring base on at least one diameter. 16. The rotor according to claim 15, wherein the rotor blade ring further includes a platform and wherein the ring base is attached to the platform and further wherein a width of the ring base in the circumferential direction is approximately equal to a width of the platform in the circumferential direction. 17. The rotor according to claim 15, wherein the ring base includes a second projection and wherein the projection extends radially inward at a first radial distance on the ring base and the second projection extends radially inward at a second radial distance on the ring base. 18. A rotor of a turbine-type machine, comprising: a rotor base body, wherein a groove is defined between a profiled wall leg of the rotor base body and an unprofiled rib of the rotor base body and wherein the groove extends in a circumferential direction of the rotor base body; and an integrally bladed and circumferentially closed rotor blade ring having a ring base, wherein the ring base includes a profiled supporting flank; wherein the ring base is secured in the groove with the profiled wall leg of the rotor base body contacting the profiled supporting flank of the ring base; wherein the ring base includes a first projection extending radially inward at a first radial distance on the ring base and a second projection extending radially inward at a second radial distance on the ring base; and wherein the rotor base body includes a second unprofiled rib on the profiled wall leg and wherein the first projection engages with the unprofiled rib and the second projection engages with the second unprofiled rib. 19. A method for securing an integrally bladed and circumferentially closed rotor blade ring of a turbine-type machine to a rotor base body, wherein a groove is defined between a profiled wall leg of the rotor base body and an unprofiled rib of the rotor base body, wherein the groove extends in a circumferential direction of the rotor base body, wherein the groove and/or the rotor base body has at least one threading opening on at least one diameter, and further wherein the rotor blade ring has a ring base that includes a profiled supporting flank, comprising the steps of: placing a projection of the ring base through the at least one threading opening; placing the ring base in the groove of the rotor base body; and engaging the profiled supporting flank of the ring base with the profiled wall leg of the rotor base body. 20. The method according to claim 19: wherein the rotor base body includes a second unprofiled rib on the profiled wall leg; wherein the ring base includes a second projection and wherein the projection extends radially inward at a first radial distance on the ring base and the second projection extends radially inward at a second radial distance on the ring base; and further comprising the steps of engaging the projection with the unprofiled rib and engaging the second projection with the second unprofiled rib.
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이 특허에 인용된 특허 (1)
Agram Daniel (Melun FRX) Charbonnel Jean-Louis (Boissise le Roi FRX) Joly Philippe G. E. (Vaux le Penil FRX) Miraucourt Grard G. (Brie Comte Robert FRX) Naudet Jacky S. (Bondoufle FRX) Prato Jean-Cla, Annular gasket disposed at one axial extremity of a rotor and covering blade feet.
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