Intakes of aerospace propulsors

An air intake (10) suitable for an aerospace propulsor comprises a duct (11) which contains, in flow series, a liquid oxygen injector (16) and two heat exchangers (17, 18). At low altitude, liquid oxygen directed into the air flow through the duct (11) via the injector (16), by reducing the air temp...

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Bibliographische Detailangaben
1. Verfasser:	JOHN LANFEAR SCOTT-SCOTT
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	An air intake (10) suitable for an aerospace propulsor comprises a duct (11) which contains, in flow series, a liquid oxygen injector (16) and two heat exchangers (17, 18). At low altitude, liquid oxygen directed into the air flow through the duct (11) via the injector (16), by reducing the air temperature to -50 DEG C or lower, causes water therein to be converted into small dry ice crystals which pass through the heat exchangers (17, 18) without any tendency to melt. Ice accretion on the heat exchangers (17, 18) is thereby avoided. At high altitude and high speed, the liquid oxygen injection is adjusted to reduce the air temperature to a level at which heat damage to the heat exchangers (17, 18) is substantially avoided.