$\require{mediawiki-texvc}$
  • 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"
쳇봇 이모티콘
안녕하세요!
ScienceON 챗봇입니다.
궁금한 것은 저에게 물어봐주세요.

특허 상세정보

Half-plow vortex generators for rotorcraft blades for reducing blade-vortex interaction noise

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-023/00   
미국특허분류(USC) 244/199 ; 244/130 ; 244/200
출원번호 US-0693579 (1996-08-07)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Radke
인용정보 피인용 횟수 : 16  인용 특허 : 0
초록

In one embodiment for a helicopter main rotor assembly, a half-plow vortex generator is mounted in combination with the upper aerodynamic surface of each main rotor blade and is operative to generate a primary corotating vortex of sufficient strength to interact with and dissipate the tip vortex generated by the same main rotor blade, thereby reducing blade-vortex interaction noise radiating from the helicopter main rotor assembly. The half-plow vortex generator has a right triangular planform configuration defined by a length, a width, and an apex angle...

대표
청구항

[ What is claimed is:] [1.] A vortex generator system for use with a rotor blade defined by a tip chord, comprising:a half-plow vortex generator having a right triangular planform configuration;said right triangular planform configuration being defined by a length, a width, and an apex angle, and an apex height;said apex height, in combination with said length, said width, and said apex angle of said right triangular planform configuration defining the three-dimensional configuration of said half-plow vortex generator; and whereinsaid half-plow vortex ge...

이 특허를 인용한 특허 피인용횟수: 16

  1. Clingman, Dan J.. Apparatus and method for generating vortexes in fluid flow adjacent to a surface. USP2011118047233.
  2. Thompson, Robert Ian. Arrangement for effecting movement of a wing tip device between a flight configuration and a ground configuration. USP20181110137977.
  3. Enthammer, Walter. Blade for a turbomachine. USP2014128899938.
  4. Whitley, L. Blake; Hoofard, Richard K.. Fan blades and associated blade tips. USP2017089726192.
  5. Whitley, L. Blake. Fan with fan blade mounting structure. USP2018019874214.
  6. Day, Daryl; Hoofard, Richard K.; Walford, Brett A.. Fire control systems. USP2014098842000.
  7. Fujino Michimasa,JPX ; Kawamura Yuichi,JPX. Flow separator reducer. USP2000106126118.
  8. Betzina, Mark D.; Nguyen, Khanh Q.. Method and system for active noise control of tiltrotor aircraft. USP2003126671590.
  9. Kovalsky,David A.; Viola,Kevin P.. Mission replaceable rotor blade tip section. USP2007077246998.
  10. Egolf T. Alan ; Wake Brian E.. Ovate loop for rotary-wing blades. USP2001076260809.
  11. Beckman, Brian C.; Kimchi, Gur; Ko, Allan. Propeller blade indentations for improved aerodynamic performance and sound control. USP20180710011346.
  12. Beckman, Brian C.; Kimchi, Gur; Ko, Allan. Propeller blade leading edge serrations for improved sound control. USP20181010099773.
  13. Beckman, Brian C.; Kimchi, Gur; Ko, Allan. Propeller blade trailing edge fringes for improved sound control. USP20190410259562.
  14. Beckman, Brian C.; Kimchi, Gur; Ko, Allan. Propeller surface area treatments for sound dampening. USP20190410259574.
  15. Narramore, Jimmy Charles. Retractable vortex generator. USP2011027878457.
  16. Irving,Jan; Davies,Robert. Wing tip device. USP2007107275722.