[특허]System and method for a fluidic barrier on the low pressure side of a fan blade

Rolls-Royce North American Technologies Inc.

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System and method for a fluidic barrier on the low pressure side of a fan blade

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/14 F02K-003/06 F01D-005/18 F01D-011/10 F01D-025/24 F01D-011/04 F02K-003/075
출원번호	US-0837942 (2015-08-27)
등록번호	US-9915149 (2018-03-13)
발명자 / 주소	Rice, Edward C.
출원인 / 주소	Rolls-Royce North American Technologies Inc.
대리인 / 주소	Duane Morris LLP
인용정보	피인용 횟수 : 0 인용 특허 : 50

초록

A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A fluid passage is defined between the splitters. The turbofan engine has a plurality of high pressure fluid jets originating from the low pressure side of the fan blades, the jets restricting the migration of the core stream into the bypass stream through the fluid passage.

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1. A turbofan engine having a fan portion in fluid communication with a core stream and a bypass stream of air; the core stream being: compressed by the fan portion and a core compressor portion, heated and expanded through a core turbine portion;the core turbine portion driving the fan portion and the compressor portion; the core turbine portion connected to a shaft;the bypass stream being compressed by the fan portion;the core and the bypass streams separated by an upstream splitter and a downstream splitter with the fan portion disposed axially between the upstream and downstream splitters wherein a fluid passage between the core and bypass streams is defined between the splitters; the fan portion having a plurality of blades; each of the blades of the fan portion having a high pressure side and a low pressure side; anda plurality of high pressure fluid jets originating from the low pressure side of the blades restricting the migration of the core stream into the bypass stream through the fluid passage. 2. The turbofan engine of claim 1, wherein the high pressure fluid jets originate from orifices on the low pressure side of the blades. 3. The turbofan engine of claim 2, further comprising a plurality of passages supplying high pressure compressed air to the high pressure fluid jets. 4. The turbofan engine of claim 3, wherein the plurality of passages are in fluid communication with the core compressor portion. 5. The turbofan engine of claim 1, wherein the pressure of the core stream is greater than the pressure of the bypass stream. 6. The turbofan engine of claim 2, wherein the plurality of orifices are radially proximate to the upstream and downstream splitters. 7. The turbofan engine of claim 1, further comprising a third splitter and said fan portion comprises a first and second fan, said first fan positioned between the upstream splitter and the third splitter and the second fan positioned between the third splitter and the downstream splitter. 8. The turbofan engine of claim 6, wherein the plurality of orifices extend between a trailing edge of the upstream splitter and a leading edge of the downstream splitter. 9. The turbofan engine of claim 1, further comprising a plurality of variable angle inlet guide vanes positioned proximate to the upstream splitter inhibiting the bypass stream. 10. A method of preventing pressure leakage from a core stream in a high bypass turbojet engine, comprising: dividing an ambient air stream into a bypass stream and a core stream with a upstream splitter;compressing the bypass and core streams with a fan, said fan between the upstream splitter and a downstream splitter dividing the bypass and core streams downstream of the fan; wherein the core stream has a higher pressure than the bypass stream; andinjecting a plurality of high pressure fluid jets from a low pressure side of the fan proximate the upstream and downstream splitters, said plurality of high pressure fluid jets having a directional component in a substantial opposite direction of the local velocity of the fan proximate the splitters thereby preventing pressure leakage across the fluid jets into the bypass stream. 11. The method of claim 10, further comprising restricting the bypass stream upstream of the of the fan. 12. The method of claim 11, wherein the step of restricting the bypass stream comprises rotating inlet guide vanes in the bypass stream, proximate the upstream splitter. 13. The method of claim 10, wherein the step of injecting a plurality of high pressure fluid jets comprises increasing the momentum of a fluid above the momentum of the core stream proximate the downstream splitter. 14. A turbofan engine comprising: a core duct defining a portion of a core fluid path;a bypass duct defining a portion of a bypass fluid path, the bypass duct concentric with the core duct and radially displaced from the core duct;a upstream splitter defining an annular first border portion between the core duct and the bypass duct;a downstream splitter defining an annular second border portion between the core duct and the bypass duct;a border region extending between a trailing edge of the upstream splitter and a leading edge of the downstream splitter;a plurality of fan blades rotating through the core duct, the bypass duct, and the border region about an axis concentric with the core and bypass ducts, each of the plurality of fan blades having a high pressure side and a low pressure side; and each of the plurality of fan blades comprise a plurality of high pressure ports positioned on the low pressure side proximate the border region; the plurality of high pressure ports connected to a high pressure fluid source by passages within each of the fan blades; and wherein the ports are configured to inject high speed fluid streams tangentially into the border region. 15. The turbofan engine of claim 14, further comprising a compressor, a combustor and a turbine along the core fluid path downstream of the downstream splitter. 16. The turbofan engine of claim 14, further comprising a plurality of inlet guide vanes in the bypass duct upstream of the plurality of fan blades, wherein the plurality of inlet guide vanes are selectively rotatable about the radial direction. 17. The turbofan engine of claim 15, wherein the passages are in fluid communication with the compressor. 18. The turbofan engine of claim 14, wherein a pressure of the core duct is greater than the pressure of the bypass duct at the border region. 19. The turbofan engine of claim 14, further comprising a third border portion and said plurality of fan blades comprises a first and second fan, said first fan positioned between the first border portion and the third border portion and the second fan positioned between the third border portion and the second border portion.

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System and method for a fluidic barrier on the low pressure side of a fan blade

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System and method for a fluidic barrier on the low pressure side of a fan blade

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