• 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Gas turbine engine mid turbine frame with flow turning features

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02D-001/00    F01D-009/04    F01D-025/28    F02K-003/06   
미국특허분류(USC) 060/796; 415/191
출원번호 US-0221450 (2014-03-21)
등록번호 US-8915090 (2014-12-23)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds, P.C.
인용정보 피인용 횟수 : 2  인용 특허 : 18

A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The an...


1. A gas turbine engine comprising: a turbine section disposed about a rotational axis; anda circumferential array of stationary airfoils arranged within the turbine section with at least one of the airfoils having a curvature provided equidistantly between pressure and suction sides and extending from a leading edge to a trailing edge at a midspan plane along the airfoil, and an angle defined between first and second lines respectively tangent to the curvature at the airfoil leading and trailing edges, the angle being equal to or greater than 10°, where...

이 특허에 인용된 특허 (18)

  1. Tibbott, Ian; Dane, Edwin. Aerofoils. USP2010127850428.
  2. Hurst, Andrew James; Harding, Simon Charles. Airfoil for a second stage nozzle guide vane. USP2010017648334.
  3. Clarke, Samuel John. Airfoil for a third stage nozzle guide vane. USP2010057722329.
  4. Chaplin Gary F. (Vernon CT) Lucas ; Jr. Arthur W. (West Hartford CT). Annular stator structure for a rotary machine. USP1988024722184.
  5. Zelesky Mark F. ; Mongillo ; Jr. Dominic J.. Coolable airfoil structure. USP2001056234754.
  6. Charles R. LeJambre ; Bruce P. Biederman ; Aaron J. Gleixner ; Chad J. Yetka. Flow directing element for a turbine engine. USP2002046375419.
  7. Orlando,Robert Joseph; Moniz,Thomas Ory; Lee,Ching Pang; Cherry,David Glenn; Beacock,Robert John; Clifford,William Larson; Carson,Scott Michael. Forward tilted turbine nozzle. USP2009037510371.
  8. Schilling, Jan Christopher. Gas turbine engine assembly and method of assembling same. USP2010047694505.
  9. Shahpar, Shahrokh; Taylor, Mark D. Guide vane for a gas turbine engine. USP2004066755612.
  10. Trindade, Ricardo; Vlasic, Edward; Girgis, Sami. HP turbine vane airfoil profile. USP2009117611326.
  11. Merry Brian. Method for forming a cooling passage and for cooling a turbine section of a rotary machine. USP2001076254333.
  12. Durocher, Eric; Pietrobon, John; Nguyen, Lam. Mid turbine frame system for gas turbine engine. USP2011118061969.
  13. Wood Peter J. ; Decker John J. ; Steinmetz Gregory T. ; Mielke Mark J. ; Seitzer Kenneth E.. Narrow waist vane. USP2001116312219.
  14. Hanson Donald B.. Noise reducing stator assembly for a gas turbine engine. USP1999045894721.
  15. Pask, George. Nozzle guide vane for a gas turbine engine. USP2011057934900.
  16. Turner,Mark Graham; Orkwis,Paul David; Cedar,Richard David. Row of long and short chord length and high and low temperature capability turbine airfoils. USP2006087094027.
  17. Pannone John L. (Glastonbury CT) Tommasini Rocco M. (Marlborough CT). Temperature and pressure probe. USP1988084765751.
  18. Praisner, Thomas J.; Allen-Bradley, Eunice; Magge, Shankar S.; Kumar, Keshava B.. Turbine vane airfoil with turning flow and axial/circumferential trailing edge configuration. USP2011128075259.