Heat Exchanger Design in Combined Cycle Engines

From The Space Library

Author - H. Webber et al

Co-Author(s) - H. Webber; S. Feast; A. Bond

JBIS Volume # - 62

Page # - 122-130

Year - 2009

Keywords - Heat exchangers, precoolers, combined cycle engines, SABRE engine

JBIS Reference Code # - 2009.62.122

Number of Pages - 9

[edit] Abstract

Combined cycle engines employing both pre-cooled air-breathing and rocket modes of operation are the most promising propulsion system for achieving single stage to orbit vehicles. The air-breathing phase is purely for augmentation of the mission velocity required in the rocket phase and as such must be mass effective, re-using the components of the rocket cycle, whilst achieving adequate specific impulse. This paper explains how the unique demands placed on the air-breathing cycle results in the need for sophisticated thermodynamics and the use of a series of different heat exchangers to enable precooling and high pressure ratio compression of the air for delivery to the rocket combustion chambers. These major heat exchanger roles are; extracting heat from incoming air in the precooler, topping up cycle flow temperatures to maintain constant turbine operating conditions and extracting rejected heat from the power cycle via regenerator loops for thermal capacity matching. The design solutions of these heat exchangers are discussed.

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