IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0362689
(2009-01-30)
|
등록번호 |
US-8162603
(2012-04-24)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
5 |
초록
▼
A vane frame for a turbomachine and a method for minimizing the weight of a vane frame. The vane frame includes an inner shroud made up of a plurality of inner shroud segments, an outer shroud circumscribing the inner shroud and made up of a plurality of outer shroud segments, and guide vanes struct
A vane frame for a turbomachine and a method for minimizing the weight of a vane frame. The vane frame includes an inner shroud made up of a plurality of inner shroud segments, an outer shroud circumscribing the inner shroud and made up of a plurality of outer shroud segments, and guide vanes structurally interconnecting the inner and outer shrouds. The guide vanes include a plurality of first guide vanes between and connecting first pairs of the inner and outer shroud segments, and a plurality of second guide vanes between and connecting second pairs of the inner and outer shroud segments. The first and second guide vanes are formed of different first and second materials, respectively, with the first material having lower strength, modulus, and/or density than the second material. The structural interconnection between the inner and outer shrouds is dominated by the second guide vanes.
대표청구항
▼
1. A vane frame for a turbomachine, the vane frame comprising: an inner shroud comprising a plurality of inner shroud segments;an outer shroud circumscribing the inner shroud and comprising a plurality of outer shroud segments; andguide vanes structurally interconnecting the inner and outer shrouds,
1. A vane frame for a turbomachine, the vane frame comprising: an inner shroud comprising a plurality of inner shroud segments;an outer shroud circumscribing the inner shroud and comprising a plurality of outer shroud segments; andguide vanes structurally interconnecting the inner and outer shrouds, the guide vanes comprising a plurality of first guide vanes between and connecting first pairs of the inner and outer shroud segments, and a plurality of second guide vanes between and connecting second pairs of the inner and outer shroud segments, the first guide vanes and the first pairs of the inner and outer shroud segments to which they are connected being formed of a first material and the second guide vanes and the second pairs of the inner and outer shroud segments to which they are connected being formed of a second material that is different from the first material, the first material having lower strength and modulus than the second material, and the structural interconnection between the inner and outer shrouds being dominated by the second guide vanes and the second pairs of the inner and outer shroud segments to which they are connected. 2. The vane frame according to claim 1, wherein the first material is a composite material and the first guide vanes and the first pairs of the inner and outer shroud segments are formed as a unitary molded component. 3. The vane frame according to claim 1, wherein the second material of the second guide vanes and the second pairs of the inner and outer shroud segments is a metallic material. 4. The vane frame according to claim 1, wherein the first guide vanes comprise a first group of the first guide vanes that are commonly between and connected to one of the first pairs of the inner and outer shroud segments and define a vane sector therewith. 5. The vane frame according to claim 4, wherein at least some of the first guide vanes of the vane sector have different cambers. 6. The vane frame according to claim 5, wherein the first guide vanes of the vane sector have cambers that differ by about +1 to about +5 degrees between adjacent pairs of the first guide vanes. 7. The vane frame according to claim 5, wherein the first guide vanes of the vane sector have increasing cambers from one end of the vane sector to another end of the vane sector. 8. The vane frame according to claim 1, wherein the first guide vanes comprise multiple groups of the first guide vanes, and each multiple group is commonly between and connected to a corresponding one of the first pairs of the inner and outer shroud segments and define a vane sector therewith. 9. The vane frame according to claim 1, wherein the second guide vanes comprise a first group of the second guide vanes that are commonly between and connected to one of the second pairs of the inner and outer shroud segments and define a vane sector therewith. 10. The vane frame according to claim 1, wherein the second guide vanes comprise at least one individual guide vane that is exclusively between and connected to one of the second pairs of the inner and outer shroud segments and define a vane sector therewith. 11. The vane frame according to claim 1, wherein the second guide vanes are approximately equi-angularly interspersed among the first guide vanes. 12. The vane frame according to claim 1, wherein the second guide vanes account for not more than 25% of all of the guide vanes of the vane frame. 13. The vane frame according to claim 1, wherein the vane frame is installed in a high-bypass duct of the turbomachine and aft of a fan of the turbomachine. 14. The vane frame according to claim 13, wherein the turbomachine comprises a core engine and a fan nacelle, the vane frame structurally interconnects and supports the fan nacelle from the core engine, and at least one of the inner and outer shroud segments comprises embossments that radially extend therefrom and engage and secure the vane frame to at least one of a fan casing of the fan nacelle or an inner frame of the core engine. 15. The vane frame according to claim 14, wherein at least 75% of the load applied to the vane frame by the fan nacelle is transmitted to the core engine by the second guide vanes. 16. The vane frame according to claim 13, wherein the turbomachine is a high-bypass turbofan engine. 17. A method of reducing the weight of a vane frame for a turbomachine, the vane frame comprising an inner shroud comprising a plurality of inner shroud segments, an outer shroud circumscribing the inner shroud and comprising a plurality of outer shroud segments, and guide vanes structurally interconnecting the inner and outer shrouds, the method comprising: forming a plurality of first guide vanes of the guide vanes that are between and connect first pairs of the inner and outer shroud segments, and forming a plurality of second guide vanes of the guide vanes that are between and connect second pairs of the inner and outer shroud segments, wherein the first guide vanes and the first pairs of the inner and outer shroud segments to which they are connected are formed of a first material and the second guide vanes and the second pairs of the inner and outer shroud segments to which they are connected are formed of a second material that is different from the first material, the first material has a lower density than the second material, the vane frame comprises more of the first guide vanes than of the second guide vanes, and the structural interconnection between the inner and outer shrouds is dominated by the second guide vanes and the second pairs of the inner and outer shroud segments to which they are connected. 18. The method according to claim 17, wherein the first material is a composite material and a first group of the first guide vanes is commonly between and unitarily molded with one of the first pairs of the inner and outer shroud segments to define a unitary molded vane sector. 19. The method according to claim 18, wherein at least some of the first guide vanes of the vane sector are fabricated to have different cambers. 20. The method according to claim 17, further comprising installing the vane frame in a high-bypass duct of the turbomachine and aft of a fan of the turbomachine, wherein the turbomachine comprises a core engine and a fan nacelle and the vane frame is installed to structurally interconnect and support the fan nacelle from the core engine with embossments that radially extend from the inner and outer shroud segments and engage and secure the vane frame to a fan casing of the fan nacelle and an inner frame of the core engine.
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