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Aerotecnica Missili & Spazio

, Volume 96, Issue 1, pp 32–43 | Cite as

Parametric study on the performance of an expander bleed engine

  • M. Leonardi
  • F. Di Matteo
  • F. Nasutia
Article

Abstract

Expander bleed cycles have a rather simple configuration when compared to other engine cycles, making them appealing when a new low-thrust engine must be designed. This type of cycles can only operate with light fuels that can be pumped in the liquid state and then properly expanded as a gas in the turbines. As a consequence of the limited amount of power provided by the coolant, expander cycles are characterized by a maximum thrust level of a few hundreds of kilonewtons. The present study focuses on the analysis of a liquid oxygen/liquid hydrogen expander bleed engine cycle dedicated to upper stage applications. A basic selection of all the key parameters defining the engine and its subsystems is carried out to obtain a specific configuration able to work at a prescribed working point. Starting from this configuration, a parametric analyses is performed to study the effect of single component properties and modelling on the expected overall engine performance.

Nomenclature

mass flow rate

a

pump head coefficient

AR

aspect ratio

cp

specific heat at constant pressure

D

diameter

F

thrust

F/W

thrust to weight ratio

h

height

Isp

specic impulse

L

length

m

mass

N

number

O/F

mixture ratio

p

pressure

T

temperature

t

thickness

w

width

x

turbine mass flow rate fraction

α

conic nozzle expansion angle

η

efficiency

ρ

density

θ

conic nozzle contraction angle

ε

expansion ratio

εc

contraction ratio

Subscripts

c

chamber

cc

cooling channels

conv

convergent

e

exit

f

fuel

fin

fin

max

maximum

o

oxidizer

p

pump

sup

supersonic

t

turbine

tank

tank

th

throat

tot

total

wall

wall

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Copyright information

© AIDAA Associazione Italiana di Aeronautica e Astronautica 2017

Authors and Affiliations

  • M. Leonardi
    • 1
  • F. Di Matteo
    • 2
  • F. Nasutia
    • 1
  1. 1.Dipartimento di Ingegneria Meccanica e Aerospaziale“Sapienza” - Università di RomaFrance
  2. 2.The Netherlands Aerothermodynamic & Propulsion Analysis SectionESA-ESTECNoordwijkThe Netherlands

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