Gas turbine with free-running generator driven by by-pass gas flow
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-006/00
출원번호
UP-0587822
(2005-01-29)
등록번호
US-7721555
(2010-06-14)
우선권정보
DE-10 2004 004 945(2004-01-31)
국제출원번호
PCT/DE2005/000137
(2005-01-29)
§371/§102 date
20060728
(20060728)
국제공개번호
WO05/073519
(2005-08-11)
발명자
/ 주소
Sharp, John
Kreiner, Andreas
출원인 / 주소
MTU Aero Engines GmbH
대리인 / 주소
Davidson, Davidson & Kappel, LLC
인용정보
피인용 횟수 :
11인용 특허 :
3
초록▼
A gas turbine, especially an aircraft engine is provided. The gas turbine comprises at least one compressor (15, 16), at least one combustion chamber (17), at least one turbine (18, 19), and at least one generator (20) for generating electrical energy, each generator (20) comprising at least one sta
A gas turbine, especially an aircraft engine is provided. The gas turbine comprises at least one compressor (15, 16), at least one combustion chamber (17), at least one turbine (18, 19), and at least one generator (20) for generating electrical energy, each generator (20) comprising at least one stator (25) and at least one rotor (22). Each rotor (22) of each generator (20) is embodied as a free-wheeling generator turbine that is driven by a gas flow in such a way that it rotates in relation to the respective stator (25) of the respective generator (20) and thus generates electrical energy from the kinetic energy of the gas flow.
대표청구항▼
What is claimed is: 1. A gas turbine comprising: at least one compressor; at least one combustion chamber; at least one turbine; and at least one generator for generating electrical energy, the at least one generator including at least one rotor and at least one corresponding stator, the at least o
What is claimed is: 1. A gas turbine comprising: at least one compressor; at least one combustion chamber; at least one turbine; and at least one generator for generating electrical energy, the at least one generator including at least one rotor and at least one corresponding stator, the at least one rotor being a free-running generator turbine which, driven by a gas flow, rotates relative to its corresponding stator and generates electrical energy from the kinetic energy of the gas flow; and a fan module having at least one fan and a fan flow channel, a part of the gas flow from the fan module passing to the at least one compressor and another part of the pass flow passing to the fan flow channel and bypassing the at least one compressor to define a bypass gas flow, the at least one generator being positioned downstream from the at least one fan such that the at least one generator is driven by the bypass gas flow. 2. The gas turbine as recited in claim 1, wherein the at least one rotor includes a plurality of rotors. 3. The gas turbine as recited in claim 2, wherein the at least one generator is integrated into a generator module, the generator module being detachably connected to the fan module. 4. The gas turbine as recited in claim 1, wherein the at least one rotor has multiple rotating blades, each blade being assigned a corresponding pole piece. 5. The gas turbine as recited in claim 4, wherein the pole pieces are assigned to radially outside ends of the rotating blades of the or each rotor, the at least one corresponding stator radially enclosing its rotor. 6. The gas turbine as recited in claim 4, wherein in that the pole pieces are assigned to radially inside ends of the rotating blades of the or each rotor, the at least one rotor radially enclosing its corresponding stator. 7. The gas turbine as recited in claim 1, wherein the at least one rotor has a smaller number of blades than the or each fan of the fan module. 8. The gas turbine as recited in claim 2, wherein the at least one generator has multiple generator stages, each generator stage including one of the plurality of rotors. 9. The gas turbine as recited in claim 1, wherein the blades of the at least one rotor are adjustable for adjusting the angle of incidence of the blades. 10. The gas turbine as recited in claim 1, wherein the at least one generator includes a first generator and a second generator, the first generator being positioned downstream from the fan module and the second generator being positioned downstream from a low pressure turbine, and wherein kinetic energy of the gas flow exiting the fan module and kinetic energy of the gas flow exiting the low pressure turbine are converted into electrical energy.
Beutin, Bruno Albert; Colin, Antoine Olivier Francois; Reaux, Clarisse Savine Mathilde; Yvon, Didier Jean-Louis, Turbine engine with a power turbine equipped with an electric power generator centered on the axis of the turbine engine.
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