Gas turbine engine airfoil total chord relative to span
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/14
F02C-003/04
출원번호
US-0624240
(2015-02-17)
등록번호
US-9347323
(2016-05-24)
발명자
/ 주소
Gallagher, Edward J.
Monzon, Byron R.
Liu, Ling
Li, Linda S.
Whitlow, Darryl
Ford, Barry M.
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
3인용 특허 :
43
초록▼
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm).
대표청구항▼
1. An airfoil for a turbine engine comprising: pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a total chord length and a span position correspo
1. An airfoil for a turbine engine comprising: pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a total chord length and a span position corresponding to a curve having an increasing total chord length from the 0% span position to a first peak, the first peak occurs in the range of 45-65% span position, the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position, wherein the total chord length at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm), wherein the total chord length includes a maximum differential between the maximum and minimum chord lengths along the entire span in the range of 3.0-4.0 inches (7.6-10.2 cm). 2. The airfoil according to claim 1, wherein the curve is at least a third order polynomial having an initial positive slope. 3. The airfoil according to claim 1, wherein the peak is provided by a first critical point in a range of 60-65% span position. 4. The airfoil according to claim 3, wherein a negative slope extends from the critical point to a second critical point in a range of 80-90% span position. 5. The airfoil according to claim 4, wherein the second critical point has an L/Rd ratio in the range of 0.32 to 0.35. 6. The airfoil according to claim 4, wherein a positive slope extends from the second critical point to the 100% span position, the total chord length at the 100% span position less than the total chord length at the peak. 7. The airfoil according to claim 1, wherein the peak is provided by a critical point in a range of 50-60% span position. 8. The airfoil according to claim 7, wherein a slope from the critical point to an inflection point is substantially zero, the inflection point in a range of 70-80% span position. 9. The airfoil according to claim 8, wherein a positive slope extends from the inflection point to the 100% span position. 10. The airfoil according to claim 9, wherein the 100% span position has an L/Rd ratio in the range of 0.38 to 0.42. 11. The airfoil according to claim 9, wherein the positive slope extending from the inflection point to the 100% span position is constant. 12. The airfoil according to claim 1, wherein the peak is provided by a critical point in a range of 40-50% span position. 13. The airfoil according to claim 12, wherein a negative slope extends from the critical point to the 100% span position. 14. The airfoil according to claim 13, wherein the negative slope is constant from about a 55% span position to the 100% span position. 15. The airfoil according to claim 12, wherein the critical point has an L/Rd ratio in the range of 0.39 to 0.43. 16. The airfoil according to claim 1, wherein the airfoil is a fan blade for a gas turbine engine. 17. A gas turbine engine comprising: a combustor section arranged between a compressor section and a turbine section;a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a low fan pressure ratio of less than 1.55;a geared architecture coupling the fan section to the turbine section or compressor section; andwherein the fan blades include an airfoil having pressure and suction sides, the airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a total chord length and a span position corresponding to a curve having an increasing total chord length from the 0% span position to a first peak, the first peak occurs in the range of 45-65% span position the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position, wherein the total chord length at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm), wherein the total chord length includes a maximum differential between the maximum and minimum chord lengths along the entire span in the range of 3.0-4.0 inches (7.6-10.2 cm). 18. A gas turbine engine comprising: a combustor section arranged between a compressor section and a turbine section;a fan section has alow fan pressure ratio of less than 1.55; andwherein the fan blades include an airfoil having pressure and suction sides, the airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a total chord length and a span position corresponding to a curve having an increasing total chord length from the 0% span position to a first peak, the first peak occurs in the range of 45-65% span position the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position, wherein the total chord length at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm), wherein the total chord length includes a maximum differential between the maximum and minimum chord lengths along the entire span in the range of 3.0-4.0 inches (7.6-10.2 cm). 19. The gas turbine engine according to claim 18, wherein the low fan pressure ratio is less than 1.52. 20. The gas turbine engine according to claim 19, wherein the low fan pressure ratio is less than 1.50. 21. The gas turbine engine according to claim 20, wherein the low fan pressure ratio is less than 1.48. 22. The gas turbine engine according to claim 21, wherein the low fan pressure ratio is less than 1.46. 23. The gas turbine engine according to claim 22, wherein the low fan pressure ratio is less than 1.44.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (43)
Wood, Peter John; Falk, Eric Andrew; Dailey, Lyle D., Advanced booster rotor blade.
Weingold Harris D. (West Hartford CT) Neubert Robert J. (Amston CT) Andy John G. (Hamden CT) Behlke Roy F. (Manchester CT) Potter Glen E. (Vernon CT), Bowed airfoil for the compression section of a rotary machine.
Orosa, John; Montgomery, Matthew, Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1:1 to 3:1 along the radially outer portion.
Liu Hsin-Tuan ; Dickman Robert B. ; Krabacher Kenneth W. ; Steinmetz Gregory T. ; Beacher Brent F. ; Doloresco Bryan K., Doubled bowed compressor airfoil.
Wadia Aspi R. (Loveland OH) Szucs Peter N. (West Chester OH) Niskode Padmakar M. (Cincinnati OH) Battle Pamela A. (Forest Park OH), Forward swept rotor blade.
Burton, Scott Andrew; Prakash, Chander; Machnaim, Joseph; Cherry, David Glenn; Beacock, Robert John; Lee, Ching-Pang; Carson, Scott Michael, Gas turbine engines including multi-curve stator vanes and methods of assembling the same.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.