IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0609680
(2009-10-30)
|
등록번호 |
US-8449260
(2013-05-28)
|
발명자
/ 주소 |
- Xie, Ming
- Neis, Scott Francis
- Slusher, Steven Todd
- Blanton, Lee Alan
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
9 |
초록
▼
Composite load-bearing rotating rings suitable for use in fan sections of gas turbine engines, and processes for their fabrication. Such a ring has at least a first portion defining an integral abutment surface adapted to abut and retain hardware of a rotating machine, at least a second portion defi
Composite load-bearing rotating rings suitable for use in fan sections of gas turbine engines, and processes for their fabrication. Such a ring has at least a first portion defining an integral abutment surface adapted to abut and retain hardware of a rotating machine, at least a second portion defining an integral flange adapted to secure the ring to a support structure of the rotating machine, and an insert. Each of the first and second portions and the insert contains a polymer matrix material and a fibrous reinforcement material, and the fibrous reinforcement material within the insert is oriented predominantly in a circumferential direction of the ring for carrying both circumferential and radial loads during rotation of the ring.
대표청구항
▼
1. A process comprising fabricating a composite load-bearing rotating ring for a rotating machine, the fabricating step comprising: forming multiple preforms, at least a first preform of the multiple preforms having a laminate architecture containing a polymer matrix material and a fibrous reinforce
1. A process comprising fabricating a composite load-bearing rotating ring for a rotating machine, the fabricating step comprising: forming multiple preforms, at least a first preform of the multiple preforms having a laminate architecture containing a polymer matrix material and a fibrous reinforcement material and at least a second preform of the multiple preforms containing a polymer matrix material and a fibrous reinforcement material oriented predominantly in a circumferential direction of the composite load-bearing rotating ring for carrying both circumferential and radial loads during rotation of the composite load-bearing rotating ring; and thencuring the polymer matrix materials of the first and second preforms to bond the multiple preforms together and yield the composite load-bearing rotating ring, at least a first portion of the composite load-bearing rotating ring defining an integral abutment surface adapted to abut and retain hardware of the rotating machine, at least a second portion of the composite load-bearing rotating ring defining an integral flange adapted to secure the composite load-bearing rotating ring to a support structure of the rotating machine, and the second preform forms an insert within the composite load-bearing rotating ring, the insert being located within the first portion of the composite load-bearing rotating ring defining the integral abutment surface. 2. The process according to claim 1, wherein the multiple preforms are formed to include a third preform having a laminate architecture containing a polymer matrix material and a fibrous reinforcement material, the process further comprising laminating the first and third preforms together to define the integral flange and an integral shroud of the composite load-bearing rotating ring. 3. The process according to claim 2, wherein the first and third preforms are laminated together to define a cavity therebetween, and the second preform is located within the cavity and forms the insert within the cavity as a result of the curing step. 4. The process according to claim 3, wherein the second preform is formed by fabricating a tubular-shaped fabric and then diametrically flattening the tubular-shaped fabric. 5. The process according to claim 4, wherein the tubular-shaped fabric comprises fiber tows of different diameters, the fiber tows having smaller diameters being located within a first hemisphere of the tubular-shaped fabric, and the fiber tows having larger diameters being located within a second hemisphere of the tubular-shaped fabric diametrically opposite the first hemisphere. 6. The process according to claim 5, wherein the second preform has a wedge-shaped cross-section so as to have a narrower axial end and a wider axial end, and the first and second hemispheres of the tubular-shaped fabric form the narrower and wider axial ends, respectively, of the second preform as a result of diametrically flattening the tubular-shaped fabric. 7. The process according to claim 1, further comprising installing the composite load-bearing rotating ring in a fan section of a gas turbine engine so that the integral abutment surface abuts and retains a fan platform of the fan section, and the integral flange secures the composite load-bearing rotating ring to the support structure of the fan section. 8. The process according to claim 7, further comprising installing a metallic intermediate flange between the integral flange of the composite load-bearing rotating ring and the support structure of the fan section. 9. The process according to claim 7, wherein the second portion of the composite load-bearing rotating ring further defines an integral composite rabbet that engages the support structure as a result of installing the composite load-bearing rotating ring. 10. The process according to claim 7, further comprising assembling the composite load-bearing rotating ring with a metal flange by attaching the integral flange of the composite load-bearing rotating ring to the metal flange, and then securing the metal flange to the support structure of the fan section. 11. The process according to claim 10, further comprising securing the integral flange of the composite load-bearing rotating ring to a spinner of the fan section. 12. The process according to claim 1, wherein the composite load-bearing rotating ring comprises at least a third portion that defines an integral shroud and an inner flowpath boundary surface of the rotating machine, and the first portion of the composite load-bearing rotating ring defining the integral abutment surface is a lug between the second and third portions of the composite load-bearing rotating ring. 13. The process according to claim 1, wherein the composite load-bearing rotating ring comprises at least a third portion that defines an integral shroud and an inner flowpath boundary surface of the rotating machine, and the first portion of the composite load-bearing rotating ring defining the integral abutment surface is located at a distal end of the integral shroud. 14. The process according to claim 1, further comprising: assembling the multiple preforms so that curing the polymer matrix materials of the first and second preforms produces a second composite load-bearing rotating ring bonded to the composite load-bearing rotating ring; and thenseparating the second composite load-bearing rotating ring from the composite load-bearing rotating ring. 15. A composite load-bearing rotating ring for a rotating machine, the composite load-bearing rotating ring comprising: at least a first portion defining an integral abutment surface adapted to abut and retain hardware of the rotating machine;at least a second portion defining an integral flange adapted to secure the composite load-bearing rotating ring to a support structure of the rotating machine; andan insert within the composite load-bearing rotating ring, the insert being located within the first portion of the composite load-bearing rotating ring defining the integral abutment surface;wherein each of the first and second portions and the insert of the composite load-bearing rotating ring contains a polymer matrix material and a fibrous reinforcement material, and the fibrous reinforcement material within the insert is oriented predominantly in a circumferential direction of the composite load-bearing rotating ring for carrying both circumferential and radial loads during rotation of the composite load-bearing rotating ring. 16. The composite load-bearing rotating ring according to claim 15, wherein the first portion of the composite load-bearing rotating ring defining the integral abutment surface is a lug between the second portion defining the integral flange and a third portion of the composite load-bearing rotating ring that defines an integral shroud and an inner flowpath boundary surface of the rotating machine. 17. The composite load-bearing rotating ring according to claim 15, wherein the first portion of the composite load-bearing rotating ring defining the integral abutment surface is located at a distal end of the integral shroud. 18. The composite load-bearing rotating ring according to claim 17, further comprising a second insert containing a polymer matrix material and a fibrous reinforcement material, the second insert being located radially outward of the insert and defining a scalloped contour at the inner flowpath boundary surface defined by the integral shroud.
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