Structural evaluation of a space main engine (SSME) high pressure fuel turbopump turbine blade
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Structural evaluation of a space main engine (SSME) high pressure fuel turbopump turbine blade

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Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, D.C.], [Springfield, Va .
Written in English

Subjects:

  • Space shuttle main engine.,
  • Finite element method.,
  • Structural analysis.,
  • Thermal analysis.,
  • Turbine blades.,
  • Turbine pumps.,
  • Mechanical properties.

Book details:

Edition Notes

StatementAli Abdul-Aziz.
SeriesNASA contractor report -- 198428., NASA contractor report -- NASA CR-198428.
ContributionsUnited States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15504927M

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The engine's nozzle is in ( m) long with a diameter of inches ( m) at its throat and inches ( m) at its exit. The nozzle is a bell-shaped extension bolted to the main combustion chamber, referred to as a de Laval RS nozzle has an unusually large expansion ratio (about ) for the chamber pressure. At sea level, a nozzle of this ratio would normally Associated L/V: Space Shuttle, Space Launch System. The SpaceX Raptor is a full-flow, staged-combustion, methane-fueled rocket engine manufactured by engine is powered by cryogenic liquid methane and liquid oxygen (LOX), rather than the RP-1 kerosene and LOX used in SpaceX's prior Merlin and Kestrel rocket engines. The earliest concepts for Raptor considered liquid hydrogen (LH 2) as fuel rather than methane. When this book was first drafted, the author's intention was to use it in teaching his course Marine Structural Design. The material presented in this book may be used for several MS or PhD courses, such as Ship Structural Design, Design of Floating Production Systems, Ultimate Strength of Marine Structures, Fatigue and Fracture, and Risk and. Main Office: Park Street, Suite Naperville, Illinois Tel: () Fax: ()

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