Blade arrangement for gas turbine engine
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0724629
(2003-12-02)
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우선권정보 |
GB-0029680 (2002-12-20) |
발명자
/ 주소 |
- Richards, Martyn
- Udall, Kenneth F
- Swift, Andrew
|
출원인 / 주소 |
|
대리인 / 주소 |
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인용정보 |
피인용 횟수 :
2 인용 특허 :
1 |
초록
▼
A blade arrangement for a gas turbine engine includes a plurality of blades mounted for rotation on a disc so as to extend radially therefrom and a retention member, the retention member including an attachment portion which is attached to the disc and an abutment portion for resisting forward axial
A blade arrangement for a gas turbine engine includes a plurality of blades mounted for rotation on a disc so as to extend radially therefrom and a retention member, the retention member including an attachment portion which is attached to the disc and an abutment portion for resisting forward axial movement of at least one of the blades relative to the disc. The blade arrangement further comprises restraint means spaced from the attachment portion of the retention member, for substantially preventing radially outward movement of the abutment portion of the retention member when a forward axial force is applied by the blade to the abutment portion.
대표청구항
▼
1. A blade arrangement for a gas turbine engine, the blade arrangement comprising:a plurality of blades mounted for rotation on a disc so as to extend radially outwardly therefrom; anda retention member, the retention member including an attachment portion which is attached to the disc and an abutme
1. A blade arrangement for a gas turbine engine, the blade arrangement comprising:a plurality of blades mounted for rotation on a disc so as to extend radially outwardly therefrom; anda retention member, the retention member including an attachment portion which is attached to the disc and an abutment portion for resisting forward axial movement of at least one of the blades relative to the disc;wherein the blade arrangement further comprises restraint means spaced from the attachment portion of the retention member, for substantially preventing radially outward movement of the abutment portion of the retention member when a forward axial force is applied by the blade to the abutment portion wherein the attachment portion of the retention member is located axially forwardly of the abutment portion and of the restraint means.2. A blade arrangement according to claim 1 wherein the retention member includes an arm portion which extends between the attached portion and the restraint means, the arm portion being angled at between 40° and 70° to the axial direction of the blade arrangement.3. A blade arrangement according to claim 1 wherein the retention member is shaped such that the abutment portion contacts part of the blade when a forward axial force is applied to the blade, to resist forward axial movement of the blade.4. A blade arrangement according to claim 3 wherein the geometry of the blade arrangement is such that when the blade applies a forward axial force to the abutment portion of the retention member, a vector representing the resultant force applied to the retention member passes substantially through the attachment portion of the retention member.5. A blade arrangement according to claim 4 wherein the restraint means includes a part of the retention member which is shaped such that its radial movement is substantially prevented by an adjacent part of the blade or the disc.6. A blade arrangement according to claim 1 wherein the restraint means is substantially cylindrical in shape, and the adjacent part of the fan blade or disc comprises a substantially cylindrical member, located radially outwardly of and adjacent to the restraint means, to substantially prevent radially outward movement of the restraint means.7. A blade arrangement according to claim 1, wherein the blade arrangement forms part of a low pressure compressor or fan.8. A gas turbine engine including a low pressure compressor or fan including a blade arrangement according to claim 1.9. A blade arrangement for a gas turbine engine, the blade arrangement comprising:a plurality of blades mounted for rotation on a disc so as to extend radially outwardly therefrom; anda retention member, the retention member including an attachment portion which is attached to the disc and an abutment portion for resisting forward axial movement of at least one of the blades relative to the disc;where in the blade arrangement further comprises restraint means spaced from the attachment portion of the retention member, for substantially preventing radially outward movement of the abutment portion of the retention member when a forward axial force is applied by the blade to the abutment portion wherein the retention member is shaped such that the abutment portion contacts part of the blade when a forward axial force is applied to the blade, to resist forward axial movement of the blade wherein the geometry of the blade arrangement is such that when the blade applies a forward axial force to the abutment portion of the retention member, a vector representing the resultant force applied to the retention member passes substantially through the attachment portion of the retention member wherein the restraint means includes a part of the retention member which is shared such that its radial movement is substantially prevented by an adjacent part of the blade or the disc wherein the said part of the retention member comprises a restraint member extending from a remainder of the retention member in an axially rearwards direction, the adjacent part of the blade or disc being located radially outwardly of the restraint member.10. A blade arrangement according to claim 9 wherein the abutment portion and the restraint member together comprise a portion of the restraint member which is generally L-shaped in section.11. A blade arrangement according to claim 9 wherein the attachment portion of the retention member is located axially forwardly of the abutment portion and of the restraint means.12. A blade arrangement according to claim 11 wherein the disc also includes an attachment portion, to which the retention member is attached, via a bolt arrangement, the bolt extending in the axial direction, and passing through both respective attachment portions of the retention member and the disc.13. A blade arrangement according to claim 12 wherein the restraint means includes an arm portion which extends between the attachment portion and the restraint member, the arm portion being angled at between 40° and 70° to the axial direction of the blade arrangement.14. A blade arrangement according to claim 13 wherein the arm portion includes an undercut shoulder, which is generally L-shaped in section, and of complementary shaped to a radially outer corner of the attachment portion.15. A blade arrangement according to claim 13 wherein the arm portion is substantially frustoconical in shape.16. A blade arrangement for a gas turbine engine, the blade arrangement comprising:a plurality of blades mounted for rotation on a disc so as to extend radially outwardly therefrom; anda retention member, the retention member including an attachment portion which is attached to the disc and an abutment portion for resisting forward axial movement of at least one of the blades relative to the disc;where in the blade arrangement further comprises restraint means spaced from the attachment portion of the retention member, for substantially preventing radially outward movement of the abutment portion of the retention member when a forward axial force is applied by the blade to the abutment portion wherein the restraint means comprises an elongate finger, located between the disc and the blade, the finger extending rearwardly from a remainder of the retention member, in the axial direction.17. A blade arrangement according to claim 16 wherein the retention member includes a plurality of elongate fingers each located between a blade and the disc, an elongate finger being located between each blade and the disc.
이 특허에 인용된 특허 (1)
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Ivanko Theodore (Fairfield CT), Turbine rotor assembly of ceramic blades to metallic disc.
이 특허를 인용한 특허 (2)
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Borja, Mark; Holt, Ehren B., Rotor cover plate.
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Maalouf, Fadi S.; Malmborg, Eric W.; Bintz, Matthew E., Split disk assembly for a gas turbine engine.
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