Home Research For Teachers HISTORY
Level 1
Level 2
Level 3		 PRINCIPLES
Level 1
Level 2
Level 3		 CAREER
Level 1
Level 2
Level 3
Gallery Hot Links What's New!
Web Administration and Tools

Pratt & Whitney Engines

PRATT & WHITNEY HIGH PRESSURE TURBOPUMPS
Line Replaceable Units for the Space Shuttle Main Engine

 

 

wpe1.jpg (32364 bytes)
fuel turbopump                                                     oxidizer turbopump

 

Fuel Turbopump
Propellant: Liquid Hydrogen
Speed: 36,200 psi
Discharge Pressure (max): 6,600 psi
Flow: 162 lb/sec (16,900 gpm)
Shaft Horsepower: 73,000 hp
Turbine Inlet Temperature: 1,800 °R
Service Life: 60 Missions
Design Life: 240 Missions

 

Oxidizer Turbopump
Propellant: Liquid Oxygen
Speed: 23,600 rpm
Discharge Pressure (max): 7,850 psi
Flow: 1,170 lb/sec (8,350 gpm)
Shaft Horsepower: 27,350 hp
Turbine Inlet Temperature: 1,500 °R
Service Life: 60 Missions
Design Life: 240 Missions

 

This material is copyrighted to Pratt and Whitney and they retain and reserve all rights to this material.  The use of this material by the ALLSTAR network is with permission of Pratt and Whitney.  The ALLSTAR network's copyright applies to the format used in presenting this material.  Pratt and Whitney should be contacted directly for permission to use this material.

Send all comments to aeromaster@eng.fiu.edu
© 1995-99 ALLSTAR Network. All rights reserved worldwide.

Funded in part by Used with permission from Pratt & Whitney P&Wlogo.gif (3524 bytes)

Updated: February 23, 1999