Airfoil with stepped spanwise thickness distribution
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/14
F01D-009/04
F04D-029/32
출원번호
US-0553119
(2014-11-25)
등록번호
US-9845684
(2017-12-19)
발명자
/ 주소
Warikoo, Raman
Balike, Krishna Prasad
Lobo, Keegan
Duong, Hien
Veitch, Thomas
출원인 / 주소
PRATT & WHITNEY CANADA CORP.
대리인 / 주소
Norton Rose Fulbright Canada LLP
인용정보
피인용 횟수 :
0인용 특허 :
12
초록▼
An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil. The airfoil has a spanwise distribution of maximum thicknesses of chord
An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil. The airfoil has a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil. The spanwise distribution of maximum thicknesses decreases from the root to the tip. In one aspect, the spanwise distribution is stepped between a first portion extending from the root and a second portion extending to the tip.
대표청구항▼
1. An airfoil in a gas turbine engine, the airfoil comprising: opposed pressure and suction sides joined together at chordally opposite leading and trailing edges, the pressure and suction sides extending along a span of the airfoil from a root at 0 of the span to a tip at 1 of the span,the airfoil
1. An airfoil in a gas turbine engine, the airfoil comprising: opposed pressure and suction sides joined together at chordally opposite leading and trailing edges, the pressure and suction sides extending along a span of the airfoil from a root at 0 of the span to a tip at 1 of the span,the airfoil having a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil, the spanwise distribution of the maximum thicknesses decreasing from the root to the tip, the spanwise distribution having a first portion extending from the root to at most 0.6 of the span and at least a second portion extending successively adjacent to the first portion towards the tip, the first portion having a first slope and the second portion having a second slope, the second slope being at least one order of magnitude higher than the first slope. 2. The airfoil of claim 1, wherein the second slope is 10 times higher than the first slope. 3. The airfoil of claim 1, wherein the first portion extends between 0 and ⅓ of the span of the airfoil calculated from the root. 4. The airfoil of claim 1, wherein the spanwise distribution comprises a third portion extending to the tip, the second portion being disposed spanwise between the first portion and the third portion, the third portion having a third slope different from the second slope. 5. The airfoil of claim 4, wherein the first portion extends between 0 and ⅓ of the span at the leading edge of the airfoil calculated from the root, the second portion extends between ⅓ and ½ of the span at the leading edge of the airfoil calculated from the root, and the third portion extends on a remaining of the span at the leading edge of the airfoil to the tip. 6. The airfoil of claim 4, wherein the second slope is of an order of magnitude one higher than the third slope. 7. The airfoil of claim 4, wherein the second slope is five times higher than the third slope. 8. The airfoil of claim 4, wherein the third slope is of a same order of magnitude as the second slope. 9. The airfoil of claim 4, wherein the third slope is twice the first slope. 10. An airfoil in a gas turbine engine, the airfoil comprising: opposed pressure and suction sides joined together at chordally opposite leading and trailing edges, the pressure and suction sides extending spanwise from a root to a tip of the airfoil, the root being at 0 of a span of the airfoil and the tip being at 1 of the span;the airfoil having a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil, the spanwise distribution of maximum thicknesses having three portions, a first portion extending between 0 and 33% of the span from the root, the first portion having a first slope, a second portion extending between 33% and 55% of the span starting from the root, the second portion having a second slope at least one order of magnitude higher than the first slope, a third portion extending between 55% and 100% of the span starting from the root, the third portion having a third slope higher than the first slope, the spanwise distribution having a marked transition at connections between the first, second, and third portions. 11. A gas turbine engine comprising: a plurality of rotors and a plurality of stators including each a plurality of blades disposed radially and having an airfoil portion, the airfoil portion of the blades of one of the plurality of stators and the plurality of rotors comprising: opposed pressure and suction sides joined together at chordally opposite leading and trailing edges, the pressure and suction sides extending along a span of the airfoil from a root at 0 of the span to a tip at 1 of the span, the airfoil having a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil, the spanwise distribution of maximum thicknesses decreasing from the root to the tip, the spanwise distribution having a first portion extending from the root to at most 0.6 of the span and at least a second portion extending successively adjacent to the first portion towards the tip, the first portion having a first slope and the second portion having a second slope, the second slope being at least one order of magnitude higher than the first slope. 12. The gas turbine engine of claim 11, wherein the blades are rotary blades of the rotors. 13. The gas turbine engine of claim 11, wherein the first portion extends between 0 and ⅓ of the span calculated from the root. 14. The gas turbine engine of claim 11, wherein the spanwise distribution comprises a third portion extending to the tip, the second portion being disposed spanwise between the first portion and the third portion, the third portion having a third slope different from the second slope. 15. The gas turbine engine of claim 14, wherein the first portion extends between 0 and ⅓ of the span at the leading edge of the airfoil calculated from the root, the second portion extends between ⅓ and ½ of the span at the leading edge of the airfoil calculated from the root, and the third portion extends on a remaining of the span at the leading edge of the airfoil to the tip. 16. The gas turbine engine of claim 14, wherein the second slope is of an order of magnitude one higher than the third slope. 17. The gas turbine engine of claim 14, wherein the second slope is five times higher than the third slope. 18. The gas turbine engine of claim 14, wherein the third slope is twice the first slope.
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이 특허에 인용된 특허 (12)
Dinh Cuong V. (Schenectady NY) Ruggles Stephen G. (Scotia NY), Bucket for the last stage of a steam turbine.
Bliss Donald B. (Belmont MA), Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor bla.
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