Accession Number:

ADA409900

Title:

Another Look at the Practical and Theoretical Limits of an Expander Cycle, LOX/H2 Engine

Descriptive Note:

Technical paper

Corporate Author:

AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST

Personal Author(s):

Report Date:

1999-06-16

Pagination or Media Count:

10.0

Abstract:

Advances in materials and increases in turbopump efficiencies necessitate another look at the theoretical and practical limits for growth in chamber pressure and thrust in a liquid rocket expander cycle engine. The basic equations for turbopump power and heat flux rate out of the cooling jacket are examined to determine the theoretical limits for chamber pressure using an expander cycle. Turbopump efficiencies and operating speed limits for a LOXH2 expander engine are explored to determine practical limits as applied to the chamber pressure.

Subject Categories:

  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE