[특허]Jet engine, in particular a jet engine for an aircraft

Aguilar, Michel

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특허 상세정보

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Jet engine, in particular a jet engine for an aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-005/12 F01D-017/14 F02K-009/40 F02K-007/067
미국특허분류(USC)	060/247; 060/039.38; 060/039.8; 060/039.39; 060/039.76; 060/039.78
출원번호	US-0142673 (2010-01-15)
등록번호	US-8925296 (2015-01-06)
우선권정보	FR-09 00330 (2009-01-27); FR-09 03942 (2009-08-12)
국제출원번호	PCT/EP2010/000195 (2010-01-15)
§371/§102 date	20110629 (20110629)
국제공개번호	WO2010/086091 (2010-08-05)
발명자 / 주소	Aguilar, Michel
출원인 / 주소	Aguilar, Michel
대리인 / 주소	Defillo & Associates, Inc.
인용정보	피인용 횟수 : 2 인용 특허 : 0

초록
▼

The invention relates to a jet engine (1), in particular an aircraft jet engine, including at least one combustion chamber (3). The combustion chamber (3) is connected to at least one compressed gas intake (4) and to at least one burnt gas outlet (5). Said burnt gas outlet(s) (5) include an exhaust valve. The exhaust valve includes two rotary parts (7), referred to as rotary exhaust parts, the rotary exhaust parts (7) including curved walls (8) and intermediate walls (9) connecting the curved walls (8), and rotating in a coordinated, continuous fashion such that said valve is in a closed position in order to block the gas during at least one combustion step, and in an open position in order to define a space (10) through which the gas flows out from the combustion chamber (3) during at least one expansion step.

대표
청구항
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1. A jet engine (1), in particular an aircraft jet engine, comprising: at least one enclosure (3), termed a combustion chamber, adapted to carry out combustion therein in at least one combustion step and connected to:at least one gas intake (4), termed a compressed gas intake, which makes it possible to supply the combustion chamber (3) with compressed gases in at least one filling step, and toat least one outlet (5), termed a burnt gas outlet, through which the gases are discharged from the combustion chamber in at least one expansion step,said burnt gas outlet(s) (5) comprising a valve (6), termed a discharge valve, wherein:the discharge valve (6) comprises two rotary parts (7), termed rotary discharge parts, the rotary discharge parts (7) comprising curved walls (8) and intermediate walls (9) connecting the curved walls (8) and rotating in a coordinated fashion relative to one another so as to be:in an angular position, termed a closed position, in which the curved wall (8) of the rotary discharge part (7) is in contact with the curved wall (8) of the other part, so as to counter a significant discharge of gas from the combustion chamber (3), in at least one combustion step, andin an angular position, termed an open position, in which one of the intermediate walls (9) of the rotary discharge part (7) is situated facing a wall of the other rotary discharge part (7) so as to define an open space (10) between the two walls and through which the gases are discharged from the combustion chamber (3) in at least one expansion step. 2. The jet engine as claimed in claim 1, wherein in the open position, one of the intermediate walls (9) of the rotary discharge part (7) is situated facing one of the intermediate walls (9) of the other rotary discharge part (7). 3. The jet engine as claimed in claim 2, wherein the rotary discharge parts (7) rotate directly with respect to the discharge direction of the gases from the combustion chamber (3). 4. The jet engine as claimed in claim 2 wherein the rotary discharge parts (7) are symmetrical relative to the axis of the combustion chamber (3). 5. The jet engine as claimed in claim 1, wherein the curved walls (8) of one rotary part have the same radius of curvature as the curved walls of the other rotary part. 6. The jet engine as claimed in claim 1, wherein the intermediate walls (9) of the rotary parts are convex. 7. The jet engine as claimed in claim 1, wherein the compressed gas intake (4) comprises a valve (11), termed an injection valve, which is adapted so as to counter the flow of the gases between the compressed gas intake (4) and the combustion chamber (3) in at least one combustion step. 8. The jet engine as claimed in claim 7, wherein the injection valve (11) comprises two rotary parts, termed rotary injection parts, with a structure similar to the rotary discharge parts (7), and rotating in a coordinated fashion relative to one another so as to be: in an angular position, termed the closed position, in which a curved wall (13) of a rotary injection part (12) is substantially in contact with a curved wall (13) of the other part, so as to counter a significant flow of the gases between the compressed gas intake and the combustion chamber (3), in at least one combustion step, andin an angular position, termed the open position, in which one intermediate wall (14) of the rotary injection part is situated facing an intermediate wall (14) of the other rotary injection part so as to define a space through which the compressed gases supply the combustion chamber (3), in at least one filling step. 9. The jet engine as claimed in claim 8, wherein the rotary parts of the injection valve and the discharge valve are adapted to: be in the fixed open position during several successive combustion/expansion steps, and then rotate in a coordinated and continuous fashion relative to one another so as to alternate several successive combustion/expansion cycles during which they are in the closed position in the combustion phase and then in an open position in the expansion phase. 10. The jet engine as claimed in claim 8 wherein the rotary parts of the injection valve and the discharge valve are adapted to: rotate in a coordinated and continuous fashion relative to one another so as to alternate several successive combustion/expansion cycles during which they are in the closed position in the combustion phase and then in the open position in the expansion phase, and thenin the fixed open position during several successive combustion/expansion steps. 11. The jet engine as claimed in claim 1, wherein each combustion chamber (3) comprises: at least one fuel supply (15) andat least one ignition means (16) adapted so as to ignite a mixture of fuel and compressed gases. 12. The jet engine as claimed in claim 11, further comprising multiple ignition means (16), each situated at different distances from the compressed gas intake (4), and in that said ignition means (16) are actuated in a delayed manner. 13. The jet engine as claimed in claim 1, wherein the rotary discharge parts (7) are situated in chambers, each chamber (17) having at least one opening (18) allowing the circulation of gas between the outside of said chamber (17) and the burnt gas outlet when the rotary discharge parts (7) are in the closed position. 14. The jet engine as claimed in claim 1, wherein the rotary discharge parts (7) comprise a passage which traverses them from one side to the other and is adapted so as to permit fluid to circulate through said parts. 15. The jet engine as claimed in claim 14, wherein the fluid circulating through the rotary discharge parts (7) is compressed gas which comes from the compressed gas intake (4). 16. The jet engine as claimed in claim 1, wherein some of the thermal energy emitted by the gases issuing from the burnt gas outlet (5) is used to heat the compressed gases upstream of the combustion chamber (3).

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Jet engine, in particular a jet engine for an aircraft

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Jet engine, in particular a jet engine for an aircraft

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이 특허를 인용한 특허 (2)

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IPC 상세정보(version : 201201)

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