NDLI: Thermal analysis of the mci engine turbopump

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Thermal analysis of the mci engine turbopump

Content Provider	NASA Technical Reports Server (NTRS)
Author	Roman, Jose
Copyright Year	2002
Description	The MCI Engine turbopump supplied the propellants to the main injector. The turbopump consisted of four parts; lox pump, interpropellant seal package (IPS), RP pump and turbine. The thermal analysis was divided into two 2D finite element models; Housing or stationary parts and rotor or rotating parts. Both models were analyzed at the same boundary conditions using SINDA. The housing model consisted of; lox pump housing, ips housing, RP housing, turbine inlet housing, turbine housing, exit guide vane, heat shield and both bearing outer races. The rotor model consisted of the lox impeller; lox end bearing and id race, RP impeller, and RP bearing and id race, shaft and turbine disk. The objectives of the analysis were to (1) verified the original design and recommend modifications to it, (2) submitted a thermal environment to support the structural analysis, (3) support the component and engine test program and (4) to support the X34 vehicle program.
File Size	314716
Page Count	5
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20030000753
Archival Resource Key	ark:/13960/t58d4vq7f
Language	English
Publisher Date	2002-07-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics And Thermodynamics Housings X-34 Reusable Launch Vehicle Rotors Two Dimensional Models Computerized Simulation Design Analysis Fuel Pumps Finite Element Method Turbine Pumps Thermal Environments Impellers Liquid Oxygen Thermal Analysis Liquid Propellant Rocket Engines Structural Analysis Cryogenic Rocket Propellants Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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