发明名称 |
Fuel injection assembly for a gas turbine engine |
摘要 |
A fuel injection assembly for a combustion chamber of a gas turbine engine is disclosed in which a plurality of premixing chambers are in communication with the combustion chamber and adjacent pairs of the premixing chambers are connected to a single prevapoization chamber by prevaporization conduits. Fuel is injected into the prevaporization chamber via a fuel injector and is mixed with oxidizer passing into the prevaporization chamber such that the fuel/oxidizer mixture has a richness exceeding the stoichiometric ratio. The fuel/oxidizer mixture passes into the prevaporization conduits through a diaphragm opening and, upon entering the premixing chamber, is mixed with additional oxidizer such that the fuel/oxidizer mixture in each premixing chamber has a richness less than the stoichiometric ratio. The premixing chambers are bounded by generally tubular walls, a portion of each adjacent tubular wall forming a protective hood between the fuel injector and the combustion chamber so as to prevent self-ignition of the fuel/oxidizer mixture in the prevaporization chamber. Oxidizer entering the premixing chambers passes through one or more oxidizer swirlers to assure a complete mixing of the fuel and oxidizer prior to its passing into the combustion chamber.
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申请公布号 |
US5651252(A) |
申请公布日期 |
1997.07.29 |
申请号 |
US19960601446 |
申请日期 |
1996.02.14 |
申请人 |
SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION S.N.E.C.M.A. |
发明人 |
ANSART, DENIS ROGER HENRI;COMMARET, PATRICE ANDRE;SANDELIS, DENIS JEAN MAURICE |
分类号 |
F23R3/28;F23R3/32;(IPC1-7):F23R3/32 |
主分类号 |
F23R3/28 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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