Gas turbine with magnetic shaft forming part of a generator/motor assembly
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-015/10
F02C-006/00
H02K-007/18
H02P-009/04
F03H-001/00
F02K-003/02
F02C-009/00
출원번호
US-0493705
(2009-06-29)
등록번호
US-8097972
(2012-01-17)
발명자
/ 주소
Macchia, Enzo
출원인 / 주소
Pratt & Whitney Canada Corp.
대리인 / 주소
Norton Rose OR LLP
인용정보
피인용 횟수 :
1인용 특허 :
35
초록▼
A gas turbine engine including a first shaft being one of a main shaft concentrically mounted to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom, the first shaft having a reduced diameter portion located within the gas turbine
A gas turbine engine including a first shaft being one of a main shaft concentrically mounted to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom, the first shaft having a reduced diameter portion located within the gas turbine engine, an electrical assembly having a rotor comprising permanent magnets retained on an outer surface of the reduced diameter portion and a stator comprising a magnetic field circuit disposed adjacent an outer periphery of the rotor, and an electrical connection between the magnetic field circuit and at least one of a power source and an electrically drivable accessory.
대표청구항▼
1. A gas turbine engine having a compressor section and a turbine section, comprising: a first shaft being one of a main shaft concentrically mounted to at least one turbine rotor of the turbine section and a tower shaft directly driven by the main shaft and extending generally radially therefrom, t
1. A gas turbine engine having a compressor section and a turbine section, comprising: a first shaft being one of a main shaft concentrically mounted to at least one turbine rotor of the turbine section and a tower shaft directly driven by the main shaft and extending generally radially therefrom, the first shaft having a portion located within the gas turbine engine, said portion of said first shaft having a reduced diameter relative to a remainder of said first shaft, the portion having said reduced diameter forming at least one circumferentially-extending recess in the first shaft;an electrical machine assembly having a rotor and a stator, the rotor including permanent magnets secured to an outer surface of the reduced diameter portion of the first shaft such that the permanent magnets of said rotor are received within said circumferential recess, the stator being disposed adjacent an outer periphery of the rotor and including at least one field winding, the rotor and the stator cooperating in use to provide a magnetic circuit for conducting magnetic flux around the at least one field winding; andan electrical connection between the at least one winding and at least one of a power source and a power distribution system. 2. The gas turbine engine as claimed in claim 1, wherein the permanent magnets of said rotor are secured to said outer surface of the reduced diameter portion of the first shaft in a press fit engagement. 3. The gas turbine engine as claimed in claim 1, wherein an inner diameter of the permanent magnets of said rotor is less than a nominal outer diameter of the first shaft outside said portion having the reduced diameter. 4. The gas turbine engine as claimed in claim 1, wherein the permanent magnets of said rotor are at least partially embedded within said circumferentially-extending recess. 5. The gas turbine engine as claimed in claim 1, wherein the first shaft is the main shaft, the main shaft being hollow and having an inner surface provided with at least one protrusion axially aligned with the circumferentially-extending recess, the engine further comprising a second shaft concentrically mounted to at least a second turbine rotor of the turbine section, the second shaft extending within the first shaft concentrically therewith and rotating independently therefrom, the second shaft having a second outer surface and at least one second circumferentially-extending recess therein which has a reduced diameter relative to a remainder of the second shaft, the second recess in the second shaft being axially aligned with the circumferentially-extending recess in the first shaft. 6. The gas turbine engine as claimed in claim 1, wherein the first shaft is the main shaft, and wherein the circumferentially-extending recess therein is defined at an end of the main shaft opposite of the at least one turbine rotor. 7. The gas turbine engine as claimed in claim 1, wherein the first shaft is the main shaft, and wherein said portion of the main shaft having the circumferentially-extending recess is located substantially within the compressor section of the gas turbine engine. 8. The gas turbine engine as claimed in claim 1, wherein the circumferentially-extending recess extends non-continuously about an outer circumference of the first shaft and comprises at least two separate recesses each extending around a respective portion of the outer circumference. 9. The gas turbine engine as claimed in claim 1, wherein the circumferentially-extending recess is sized relative to the permanent magnets such that an outer radius of the shaft and permanent magnets defined by an outer surface of each permanent magnet is inferior or substantially equal to an outer radius of the portion of the shaft at a location adjacent the circumferentially-extending recess. 10. A gas turbine engine comprising at least one turbine rotor and a first shaft being one of a main shaft concentrically mounted to the at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom, the first shaft having a reduced diameter portion located within the gas turbine engine and having a smaller outer diameter than that of adjacent portions of the first shaft, an electrical assembly having a rotor comprising permanent magnets retained on an outer surface of the reduced diameter portion and a stator comprising a magnetic field circuit disposed adjacent an outer periphery of the rotor, and an electrical connection between the magnetic field circuit and at least one of a power source and an electrically drivable accessory. 11. The gas turbine engine as claimed in claim 10, wherein the first shaft is hollow, the engine further comprising a second shaft extending within the first shaft concentrically therewith and rotating independently therefrom, the second shaft having a reduced diameter portion having a smaller outer diameter than that of adjacent portions of the second shaft, the reduced diameter portion of the second shaft being aligned with the reduced diameter portion of the first shaft. 12. The gas turbine engine as claimed in claim 10, wherein the first shaft is the main shaft, and the reduced diameter portion is defined at an end of the main shaft opposite of the at least one turbine rotor. 13. The gas turbine engine as claimed in claim 10, wherein the reduced diameter portion is located within a compressor section of the gas turbine engine. 14. The gas turbine engine as claimed in claim 10, wherein the reduced diameter portion is sized relative to the permanent magnets such as to prevent the permanent magnets from radially protruding beyond an outer surface of the adjacent portions of the first shaft. 15. The gas turbine engine as claimed in claim 10, wherein the first shaft is the tower shaft, and the reduced diameter portion is located in proximity of and spaced apart from an end of the tower shaft opposite of the main shaft.
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