US 9,810,153 B2
Engine
Alan Bond, Abingdon (GB); and Richard Varvill, Abingdon (GB)
Assigned to Reaction Engines Ltd, Abingdon (GB)
Filed by Reaction Engines Ltd, Abingdon (GB)
Filed on Jun. 5, 2014, as Appl. No. 14/296,624.
Claims priority of application No. 1318111.0 (GB), filed on Oct. 11, 2013.
Prior Publication US 2015/0101342 A1, Apr. 16, 2015
Int. Cl. F02C 3/04 (2006.01); F02C 7/228 (2006.01); F02C 7/04 (2006.01); F02C 7/143 (2006.01); F02K 7/18 (2006.01); F02K 9/78 (2006.01); F02C 7/08 (2006.01)
CPC F02C 7/228 (2013.01) [F02C 3/04 (2013.01); F02C 7/04 (2013.01); F02C 7/08 (2013.01); F02C 7/143 (2013.01); F02K 7/18 (2013.01); F02K 9/78 (2013.01); F05D 2220/70 (2013.01); F05D 2240/35 (2013.01); F05D 2260/20 (2013.01); F05D 2260/213 (2013.01)] 47 Claims
OG exemplary drawing
 
1. An engine comprising:
a rocket combustion chamber for the combustion of fuel and oxidant;
an air-breathing combustion chamber for the combustion of fuel and oxidant;
a compressor for pressurizing air for supply to the air-breathing combustion chamber;
a first fuel delivery system for delivering fuel to the rocket combustion chamber;
a second fuel delivery system for delivering fuel to the air-breathing combustion chamber;
an oxidant delivery system for delivering oxidant to the rocket combustion chamber;
wherein the air-breathing combustion chamber and the rocket combustion chamber are configured to be operated independently with the engine being switchable from an air-breathing mode to a full rocket mode; and
wherein the engine further comprises:
a first heat exchanger arrangement having an inlet and an outlet arranged for cooling air to be supplied to the compressor using a heat transfer medium before compression by the compressor;
a heat transfer medium loop for the heat transfer medium; and
a second heat exchanger arrangement configured for cooling of the heat transfer medium by fuel delivered by the first or second fuel delivery system.