• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    1458754 Gas turbine plant FRANCE ARMED FORCES MINISTER OF 25 Nov 1974 [4 Dec 1973] 51017/74 Headings F1G and F1L [Also in Division F4] A power unit including an internal combustion engine 1, a turbo-compressor supercharging unit 2, 3 and an auxiliary combustion chamber 5, is operated by injecting fuel into chamber 5 through an injector port 13 to be mechanically atomized when injected at a maximum rate, and continuously blowing air into a zone 9 of the chamber close to the port at a rate sufficient for the air to pneumatically atomize the fuel when supplied at a minimum rate. Air from the compressor 2 is supplied to the Diesel engine 1 through a cooler 4 and also to the combustion chamber 5 through a bypass 6 and primary or secondary air passages 8 and 10. Liquid fuel is pumped to injector 24 by a pump 14 through valves 22, 27, controlled by a thermosensitive element 23, and a pneumatic actuator 20 respectively. Exhaust gas from primary air 8 is introduced into a zone 9, secondary air is introduced, along with the exhaust gases from passage 33 leading from engine 1, into zone 10, air is supplied to vaned nozzles 15 via a passage 18, and the combustion gases from chamber 5 are supplied to turbine 3. The primary and secondary air are regulated by a spring-urged piston valve 40. Several units 2, 3, may be grouped in cascade and the turbine and compressor may have several stages.
    公开号:SU845799A3
    申请号:SU742081941
    申请日:1974-12-03
    公开日:1981-07-07
    发明作者:Мелшиор Жан；Андре Тьери
    申请人:Эта Франсе, Репрезанте Пар Ле Делегеминистерьель Пур Л"Apmemah (Фирма)；
    IPC主号:
    专利说明:

    The invention relates to the field of mechanical engineering and, in particular, to means for spraying fuel in a combustion chamber of a turbocharger of pressurization in communication with an exhaust of an internal combustion engine. A device for spraying liquid fuel containing a fuel nozzle installed in a combustion chamber by a turbocharger of a pressurized fuel jet connected to a fuel pump fl. A disadvantage of the atomizer is inefficient atomization at low fuel consumption. A device for spraying liquid fuel is also known, which contains an injector installed in a combustion engine that communicates with the exhaust and is equipped with a throttle regulator of the primary combustion air nozzle and placed around the last air inlet. However, this device also does not provide efficient atomization of fuel at low fuel consumption. . The goal is achieved by the fact that the air inlets are connected to the discharge port of the turbo-compressor in front of the throttle controller. FIG. 1 - the proposed device, a longitudinal section; in fig. 2, node I of FIG. 1} in FIG. 3 - section A-A of FIG. 2. A device for spraying liquid fuel is installed in the combustion chamber 1 connected to the exhaust manifold 2 of the engine 3 internal combustion. Combustion chamber 1 is also connected to line 4 with a discharge pipe (not shown) of the turbocharger 5 and is provided with a throttle regulator 6 at the inlet. Turbocharger 5 is connected to the turbine 7 at the inlet to the outlet of the combustion chamber 1 of the combustion chamber. A hollow body 9 is installed in the front wall 8 of the combustion chamber 1, inside which the fuel nozzle 10 is located. The cavity of the body 9 is connected by a pipe 11 to the discharge port of a turbo Kcwnpeccopa in front of the throttle regulator .6. At the outlet of the cavity of the housing 9 around the nozzle of the nozzle 10 are made tangential holes 12 in the form of slots in the end wall of the housing. The front wall 8 and the cylindrical wall 13 adjacent thereto, having openings 14, form the primary zone 15. The wall 13 is installed with an annular gap in the shell 16, through which air is supplied to the openings 14, the secondary zone is located behind the primary zone 15
    17, The outer casing of chamber 1 is made double-walled with a cavity
    18, connected at the inlet of the nozzle
    19, named the conical section 20, with the line 4, and at the exit of the holes 21 with the secondary zone 17. The shell 16 is installed in the casing of the combustion chamber with an annular gap 22, through which gas from the nozzle 2 enters the secondary zone 17, Throttle regulator The torus 6 is made in the form of a cylinder 23 with openings 24 and a transverse flap 25. Inside the cylinder 23 a spring loaded spool 26 with openings 27 is placed.
    During operation of the turbocharger and the internal combustion engine 3, the air from the turbocharger 5 is directed from one side to the engine 3, and the other through the main line 4 to the combustion chamber, into which the exhaust gases of the engine 3 also inject through pipe 2 and the fuel nozzle 10 is injected. gases from the combustion chamber 1 are directed to the turbine 7, ensuring the operation of the turbocharger. The air coming from the 4 V line throttle regulator b is divided into two streams. One flow, having passed through holes 24 and 27, is guided through an annular gap between wall 13 and shell 16 to holes 14 and then enters the primary zone 15. The other flow through pipe 19 enters the cavity 18 and from it flows through holes 21 into the secondary zone 17. Flow control of each of these flows is provided by moving the cylinder 23 and changing the passage area between the conical section 20 and the flap 25. Exhaust gases flowing into the chamber 1 through the nozzle 2 from the engine 3
    To start the turbocharger when the engine is stopped, the fuel 3
    delivered through nozzle 10 at maximum flow rate. The nozzle nozzle 10 has a diameter that is sufficiently small to provide satisfactory mechanical atomization at high fuel consumption and does not provide satisfactory mechanical atomization at low fuel consumption. As the air pressure in the discharge pipe of the turbocharger 5 increases and the pressure drop in the nozzle of the nozzle 10 decreases, the flow of air through the pipe 11 into the cavity of the housing 9 increases. Air leaking out of the housing 9 through the tangential holes 12 provides pneumatic atomization of fuel at low his expenses.
    Thus, such an embodiment of the device for spraying and liquid fuel ensures its efficient operation in the combustion chamber of the turbocharger of the turbocharger of the internal combustion engine in a wide range of variation in fuel consumption.
    权利要求:
    Claims (2)
    [1]
    1. Acceptance of UK application No. 1291030, cl. F 1 V, pub. 1972.
    [2]
    2.Patent of the USSR No. 508225, class, F 02 C 7/00, published. 1971.
    B
    3
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    同族专利:
    公开号 | 公开日
    SE7415014L|1975-06-05|
    DE2456837B2|1980-07-10|
    DE2456837A1|1975-06-05|
    NL7415514A|1975-06-06|
    SE421946B|1982-02-08|
    ES432532A1|1976-09-16|
    BR7410150A|1976-06-08|
    DK142731C|1981-08-10|
    ATA945374A|1976-06-15|
    CA1032773A|1978-06-13|
    CH588013A5|1977-05-31|
    NL155626B|1978-01-16|
    DK142731B|1981-01-05|
    GB1458754A|1976-12-15|
    JPS50106018A|1975-08-21|
    PL107598B1|1980-02-29|
    IT1026776B|1978-10-20|
    DK624274A|1975-07-21|
    BE822925A|1975-06-04|
    FR2253389A5|1975-06-27|
    IN143363B|1977-11-12|
    ZA747498B|1975-12-31|
    CS198154B2|1980-05-30|
    US4004414A|1977-01-25|
    DE2456837C3|1981-03-26|
    JPS5843567B2|1983-09-28|
    DD117263A5|1976-01-05|
    AT335233B|1977-02-25|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2620621A|1946-04-06|1952-12-09|Nettel Frederick|Diesel engine having controllable auxiliary burner means to supplement exhaust gas fed to turbocharger|
    US2608051A|1947-08-25|1952-08-26|Nettel Frederick|Control system for turbocharged compression-ignition internalcombustion engines|
    US3099910A|1955-08-11|1963-08-06|Phillips Petroleum Co|Apparatus for burning fuel at shear interface between coaxial streams of fuel and air|
    US3096615A|1961-09-21|1963-07-09|Caterpillar Tractor Co|Turbocharger system for internal combustion engines|
    GB1135670A|1966-04-20|1968-12-04|Rolls Royce|Combustion chamber for a gas turbine engine|
    US3512359A|1968-05-24|1970-05-19|Gen Electric|Dummy swirl cup combustion chamber|
    US3589127A|1969-02-04|1971-06-29|Gen Electric|Combustion apparatus|
    DE2012941A1|1969-04-01|1970-10-15|Parker-Hannifin Corp., Cleveland, Ohio |Liquid fuel injector|
    US3630024A|1970-02-02|1971-12-28|Gen Electric|Air swirler for gas turbine combustor|
    US3688495A|1970-04-17|1972-09-05|Adolf Fehler|Control system for metering the fuel flow in gas turbine engines|
    FR2097437A5|1970-07-07|1972-03-03|France Etat|
    US3890088A|1970-09-17|1975-06-17|Advanced Tech Lab|Apparatus for reducing formation of oxides of nitrogen in combustion processes|
    US3826078A|1971-12-15|1974-07-30|Phillips Petroleum Co|Combustion process with selective heating of combustion and quench air|
    FR2179309A5|1972-04-06|1973-11-16|France Etat|
    US3913314A|1972-06-09|1975-10-21|Westinghouse Electric Corp|System and method for operating a gas turbine electric power plant with bypass flow fueling operation to provide improved reliability and extended apparatus life|
    US3774851A|1972-11-15|1973-11-27|Parker Hannifin Corp|Fuel head compensating valve for fuel injection nozzle|
    US3834159A|1973-08-03|1974-09-10|Gen Electric|Combustion apparatus|
    US3859787A|1974-02-04|1975-01-14|Gen Motors Corp|Combustion apparatus|
    US3921403A|1974-04-30|1975-11-25|Garrett Corp|Auxiliary air supply system and method for turbocharged engines|GB1532636A|1975-10-02|1978-11-15|Secr Defence|Combustion apparatus|
    DE2839627C2|1977-09-13|1983-11-03|Hitachi, Ltd., Tokyo|Gas burner|
    US4517802A|1977-11-25|1985-05-21|The Garrett Corporation|Turbocharger combustor method|
    GB1602869A|1977-11-25|1981-11-18|Garrett Corp|Turbocharged internal combustion engines|
    US4215549A|1977-11-25|1980-08-05|The Garrett Corporation|Turbocharger combustor system|
    FR2472082B1|1979-12-19|1982-08-20|France Etat|
    DE3046875A1|1980-12-12|1982-07-15|Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh, 7990 Friedrichshafen|"INTERNAL COMBUSTION ENGINE"|
    JPH01128483U|1988-02-25|1989-09-01|
    US6053144A|1998-11-05|2000-04-25|Caterpillar Inc.|Diesel engine with a combustor which provides combustion products to reduce NOx production in a combustion chamber|
    US20030236489A1|2002-06-21|2003-12-25|Baxter International, Inc.|Method and apparatus for closed-loop flow control system|
    US6895745B2|2003-04-04|2005-05-24|Borgwarner Inc.|Secondary combustion for regeneration of catalyst and incineration of deposits in particle trap of vehicle exhaust|
    GB0308013D0|2003-04-07|2003-05-14|Prodrive 2000 Ltd|Turbocharger|
    US20060283187A1|2004-04-06|2006-12-21|Roland Broadbent|Combustion unit for turbocharger|
    US7481048B2|2005-06-30|2009-01-27|Caterpillar Inc.|Regeneration assembly|
    US20070158466A1|2005-12-29|2007-07-12|Harmon Michael P|Nozzle assembly|
    US20070228191A1|2006-03-31|2007-10-04|Caterpillar Inc.|Cooled nozzle assembly for urea/water injection|
    US20070235556A1|2006-03-31|2007-10-11|Harmon Michael P|Nozzle assembly|
    US20080271448A1|2007-05-03|2008-11-06|Ewa Environmental, Inc.|Particle burner disposed between an engine and a turbo charger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    FR7343112A|FR2253389A5|1973-12-04|1973-12-04|
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