Gas turbine blade array with reduced acoustic output
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F04D-029/66
F01D-005/14
F04D-029/32
F01D-005/06
F01D-005/10
출원번호
US-0768839
(2013-12-18)
등록번호
US-10233948
(2019-03-19)
국제출원번호
PCT/US2013/075946
(2013-12-18)
국제공개번호
WO2014/143280
(2014-09-18)
발명자
/ 주소
Topol, David A.
Prasad, Dilip
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Cantor Colburn LLP
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
In accordance with one aspect of the disclosure, a rotor for a gas turbine engine is disclosed. The rotor may include a rotor disk and a plurality of blade extending radially outward from the rotor disk. At least one of the blades may have a physical nonuniformity. The blades may be distributed abou
In accordance with one aspect of the disclosure, a rotor for a gas turbine engine is disclosed. The rotor may include a rotor disk and a plurality of blade extending radially outward from the rotor disk. At least one of the blades may have a physical nonuniformity. The blades may be distributed about the rotor disk based on any physical nonuniformities of the blades to generate at least one decay-resistant harmonic.
대표청구항▼
1. A gas turbine engine having a rotor, the rotor comprising: a rotor disk;a plurality of blades extending radially outward from the rotor disk, at least one blade having a physical nonuniformity, the blades being distributed about the rotor disk based on any physical nonuniformities of the blades t
1. A gas turbine engine having a rotor, the rotor comprising: a rotor disk;a plurality of blades extending radially outward from the rotor disk, at least one blade having a physical nonuniformity, the blades being distributed about the rotor disk based on any physical nonuniformities of the blades to generate at least one decay-resistant harmonic; andan acoustic liner positioned proximate to the rotor and configured to attenuate the at least one decay-resistant harmonic, wherein all the plurality of blades cooperate to generate a single dominant decay-resistant harmonic. 2. The gas turbine engine of claim 1, wherein each blade of the plurality of blades has a pitch angle, a leading edge position, and an angular offset relative a circumferentially adjacent blade, the physical nonuniformity of any blade being at least one of the pitch angle, the leading edge position, and the angular offset. 3. The gas turbine engine of claim 1, wherein the plurality of blades are distributed to form a plurality of decay-resistant harmonics. 4. A gas turbine engine having a rotor, the rotor comprising: a rotor disk;a plurality of blades extending radially outward from the rotor disk, at least one blade having a physical nonuniformity, the blades being distributed about the rotor disk based on any physical nonuniformities of the blades to generate at least one decay-resistant harmonic; andan acoustic liner positioned proximate to the rotor and configured to attenuate the at least one decay-resistant harmonic, wherein the acoustic liner attenuates an amplitude of a dominant decay-resistant harmonic of the rotor. 5. The gas turbine engine of claim 1, wherein the acoustic liner attenuates an amplitude of a plurality of decay-resistant harmonics. 6. The gas turbine engine of claim 1, wherein the rotor is a fan of a gas turbine engine. 7. A method of reducing combination tone noise in a rotor of a gas turbine engine, comprising: distributing a plurality of blades about a rotor disk of the rotor such that the blades generate a decay-resistant harmonic;attenuating the decay-resistant harmonic with an acoustic liner positioned proximate to the rotor, wherein the acoustic liner attenuates an amplitude of a dominant decay-resistant harmonic of the rotor. 8. The method of claim 7, wherein the plurality of blades are distributed such that a plurality of decay-resistant harmonics are generated by the blades and the acoustic liner attenuates the plurality of decay-resistant harmonics. 9. The method of claim 7, further comprising determining a distribution of the blades based on at least one physical nonuniformity of at least one blade before distributing the blades about the rotor disk. 10. The method of claim 9, wherein each blade has a pitch angle, a leading edge position, and an angular offset relative a circumferentially adjacent blade, any physical nonuniformity of the blades used to determine blade distribution being at least one of the pitch angle, the leading edge position, and the angular offset. 11. The method of claim 7, further comprising providing the rotor as a fan of a gas turbine engine. 12. A method of mitigating combination tone noise generated by a rotor of a gas turbine engine, comprising: providing a rotor having a rotor disk and a plurality of blades extending from the rotor disk, at least one blade having a physical nonuniformity;generating a decay-resistant harmonic with a particular positioning of the blades of the rotor based on any nonuniformities of the blades; andattenuating the decay-resistant harmonic with an acoustic liner positioned proximate to the rotor, wherein the blades cooperate to generate a dominant decay-resistant harmonic. 13. The method of claim 12, wherein the attenuating step includes attenuating an amplitude of the decay-resistant harmonic with the acoustic liner. 14. The method of claim 12, wherein the blades are provided in a distribution that generates a plurality of decay-resistant harmonics and wherein the acoustic liner is configured to attenuate the plurality of decay-resistant harmonics. 15. The method of claim 12, wherein each blade has a pitch angle, a leading edge position, and an angular offset relative a circumferentially adjacent blade, any physical nonuniformities of the blades used to determine the distribution of the blades being at least one of the pitch angle, the leading edge position, and the angular offset. 16. The method of claim 12, further comprising providing the rotor as a fan of a gas turbine engine.
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이 특허에 인용된 특허 (4)
Manzi ; Jr. Robert J. ; Mathews Douglas C. ; Slomski Soter P. ; van Achterberg Johan, Acoustically improved gas turbine blade array.
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