[특허]Airfoil leading edge end wall vortex reducing plasma

General Electric Company

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Airfoil leading edge end wall vortex reducing plasma

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/18
미국특허분류(USC)	416/001; 415/010; 415/914; 416/096.A
출원번호	UP-0639876 (2006-12-15)
등록번호	US-7628585 (2009-12-16)
발명자 / 주소	Lee, Ching Pang Wadia, Aspi Rustom Cherry, David Glenn Han, Je Chin
출원인 / 주소	General Electric Company
대리인 / 주소	Andes, William Scott
인용정보	피인용 횟수 : 10 인용 특허 : 22

초록
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A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading edge region near and around a leading edge of the airfoil and near the fillet. The plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. The plasma generators may be mounted on an outer wall of the airfoil with a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. A method for operating the system includes energizing one or more plasma generators to form the plasma in steady state or unsteady modes.

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Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims: 1. A leading edge vortex reducing system comprising: a gas turbine engine airfoil extending in a spanwise direction away from an end wall, a fillet between the airfoil and the end wall, a leading edge region of the fillet near and around a leading edge of the airfoil, one or more plasma generators extending in the spanwise direction through the fillet in the leading edge region, and the plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. 2. A system as claimed in claim 1 further comprising the plasma generators being mounted on an outer wall of the airfoil. 3. A system as claimed in claim 2 further comprising: the gas turbine engine airfoil extending in a chordwise direction between the leading edge and a trailing edge of the airfoil, a first portion of the plasma generators on a pressure side of the airfoil, and a second portion of the plasma generators on a suction side of the airfoil. 4. A system as claimed in claim 3 further comprising the first and second portions each having two of the plasma generators. 5. A system as claimed in claim 1 further comprising the plasma generators including inner and outer electrodes separated by a dielectric material. 6. A system as claimed in claim 5 further comprising an AC power supply connected to the electrodes to supply a high voltage AC potential to the electrodes. 7. A system as claimed in claim 6 further comprising the dielectric material being disposed within a groove in an outer hot surface of an outer wall of the airfoil. 8. A system as claimed in claim 7 further comprising: the gas turbine engine airfoil extending in a chordwise direction between the leading edge and a trailing edge of the airfoil, a first portion of the plasma generators on a pressure side of the airfoil, and a second portion of the plasma generators on a suction side of the airfoil. 9. A system as claimed in claim 8 further comprising a high pressure turbine nozzle vane including the airfoil extending radially in a spanwise direction between radially inner and outer bands respectively and the end wall being one of the bands. 10. A system as claimed in claim 8 further comprising a high pressure turbine blade including the airfoil extending radially outwardly from an airfoil base on a blade platform and the end wall being the blade platform. 11. A leading edge vortex reducing system comprising: a vane assembly including a row of circumferentially spaced apart and radially extending gas turbine engine vanes, each of the vanes having an airfoil extending radially in a spanwise direction between radially inner and outer bands, the airfoil having an outer wall extending in a chordwise direction between opposite leading and trailing edges, fillets between the airfoil and the inner and outer bands, leading edge regions of the fillets near and around a leading edge of the airfoil, and one or more plasma generators extending in the spanwise direction through the fillets in the leading edge regions. 12. A system as claimed in claim 11 further comprising a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. 13. A system as claimed in claim 12 further comprising the plasma generators including inner and outer electrodes separated by a dielectric material. 14. A system as claimed in claim 13 further comprising an AC power supply connected to the electrodes to supply a high voltage AC potential to the electrodes. 15. A system as claimed in claim 14 further comprising the dielectric material being disposed within a groove in an outer hot surface of an outer wall of the airfoil. 16. A system as claimed in claim 11 further comprising the plasma generators including inner and outer electrodes separated by a dielectric material. 17. A system as claimed in claim 16 further comprising an AC power supply connected to the electrodes to supply a high voltage AC potential to the electrodes. 18. A system as claimed in claim 17 further comprising the dielectric material being disposed within a groove in an outer hot surface of an outer wall of the airfoil. 19. A leading edge vortex reducing system comprising: a high pressure turbine including a row of circumferentially spaced apart turbine blades, each of the turbine blades having a turbine airfoil extending radially outwardly in a spanwise direction from an airfoil base on a blade platform, the airfoil having an outer wall extending in a chordwise direction between opposite leading and trailing edges, a fillet between the airfoil and the blade platform, a leading edge region of the fillet near and around a leading edge of the airfoil, and one or more plasma generators extending in the spanwise direction through the fillet in the leading edge region. 20. A system as claimed in claim 19 further comprising a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. 21. A system as claimed in claim 20 further comprising the plasma generators including inner and outer electrodes separated by a dielectric material. 22. A system as claimed in claim 21 further comprising an AC power supply connected to the electrodes to supply a high voltage AC potential to the electrodes. 23. A system as claimed in claim 22 further comprising the dielectric material being disposed within a groove in an outer hot surface of an outer wall of the airfoil. 24. A system as claimed in claim 19 further comprising the plasma generators including inner and outer electrodes separated by a dielectric material. 25. A system as claimed in claim 24 further comprising an AC power supply connected to the electrodes to supply a high voltage AC potential to the electrodes. 26. A system as claimed in claim 25 further comprising the dielectric material being disposed within a groove in an outer hot surface of an outer wall of the airfoil. 27. A method for operating a leading edge vortex reducing system, the method comprising: energizing one or more plasma generators to form a plasma extending over a portion of a fillet in a leading edge region of a gas turbine engine airfoil, the airfoil extending in a spanwise direction away from an end wall, the fillet being between the airfoil and the end wall, and the leading edge region being near and around a leading edge of the airfoil and being near the fillet. 28. A method as claimed in claim 27 wherein the energizing further includes supplying an AC potential to inner and outer electrodes separated by a dielectric material of the plasma generator. 29. A method as claimed in claim 28 further comprising operating the plasma generator in steady state or unsteady modes. 30. A method as claimed in claim 27 further comprising using a first portion of the plasma generators mounted on a pressure side of the airfoil and a second portion of the plasma generators mounted on a suction side of the airfoil to form the plasma on the pressure and suction sides of the airfoil. 31. A method as claimed in claim 30 wherein the energizing further includes supplying an AC potential to inner and outer electrodes separated by a dielectric material of the plasma generator. 32. A method as claimed in claim 31 further comprising operating the plasma generator in steady state or unsteady modes. 33. A method for operating a leading edge vortex reducing system, the method comprising: energizing one or more plasma generators to form plasma extending over leading edge regions of fillets of a gas turbine engine airfoil, the airfoil extending radially in a spanwise direction between radially inner and outer bands, the fillets being between the airfoil and the inner and outer bands, and the leading edge regions being near and around a leading edge of the airfoil. 34. A method as claimed in claim 33 further comprising the plasma generators extending in the spanwise direction through the fillets in the leading edge regions. 35. A method as claimed in claim 33 wherein the energizing further includes supplying an AC potential to inner and outer electrodes separated by a dielectric material of the plasma generators. 36. A method as claimed in claim 35 further comprising operating the plasma generator in steady state or unsteady modes. 37. A method as claimed in claim 33 further comprising using a first portion of the plasma generators mounted on a pressure side of the airfoil and a second portion of the plasma generators mounted on a suction side of the airfoil to form plasma on the pressure and suction sides of the airfoil respectively. 38. A method as claimed in claim 37 wherein the energizing further includes supplying an AC potential to inner and outer electrodes separated by a dielectric material of the plasma generator. 39. A method as claimed in claim 33 further comprising operating the plasma generator in steady state or unsteady modes.

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이 특허를 인용한 특허 피인용횟수: 10

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Airfoil leading edge end wall vortex reducing plasma

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Airfoil leading edge end wall vortex reducing plasma

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