|Other titles||Hot fire unit.|
|Series||NASA contractor report -- NASA CR-187035., Interface control document -- DR-28.|
|Contributions||George C. Marshall Space Flight Center.|
|The Physical Object|
Get this from a library! Liquid Hydrogen Turbopump ALS Advanced Development Program: monthly progress report, DR, 20 May - 23 June [George C. Marshall Space Flight Center.;]. For the purposes of this ICD, the test article consists of the Hot Fire Drive Turbopump mounted on its test cart, readied for installation in the component test facility. It should be emphasized that the LH2 turbopump program is still in its early concept design phase. The interface criteria for the Turbopump Test article (TPA) and the Component Test Facility located at NASA, Stennis Space Center is defined by this interface Control Document (ICD). TPA ICD Volume 2 is submitted for the Cold Gas Drive Turbopump Test Article, which is generally similar but incorporates certain changes, particularly in fluid requirements and in instrumentation : Bruce Lindley. These modifications include the following: (1) the dual pump discharge arrangement was changed to a single discharge; (2) commonality of the turbine inlet manifold with the advanced launch system (ALS) liquid oxygen (LOX) TPA was dropped for this program; (3) the turbine housing flange arrangement was improved by relocating it away from the first stage nozzles; (4) a ten percent margin (five percent Author: Nancy R. Shimp and George J. Claffy.
Advanced Development Programs are being pursued by Rocketdyne, Aerojet, and Pratt & Whitney to define and validate design approaches toward producing low-cost, reliable liquid-hydrogen and liquid-oxygen turbopumps for a kN ( klb) thrust Advanced Launch : A. Csomor, C. Faulkner, F. Ferlita. An initial design of a split flow liquid hydrogen turbopump for the Dual Expander Aerospike Nozzle (DEAN) upper stage engine was completed. The engine nozzle is an annular aerospike. The engine cycle requires a combustion chamber pressure of 1, psia. The DEAN is designed to deli lbf of thrust and seconds of by: 3. This is the Final Summary Report for the Advanced Launch System (-ALS) Rocket Liquid Hydrogen Turbopump Program, Contract NAS This program was conducted by Aerojet Propulsion Division (APD) for NASA's Marshall Space Flight Center (MSFC). Authority-to-proceed (ATP) was given on 1 May APD was directed to close out the program on 6 August File Size: 2MB. A wide variety of parameters must be considered in the design of an advanced industrial or turbopump inducer. These include the optimum inlet eye diameter, the inlet blade angle, (particularly at the inducer tip), the design point incidence value, leading edge shape, and the blade number as well as the blade turning angle and.
LIST OF ACRONYMS, ABBREVIATIONS, AND SYMBOLS ADP Advanced Development Program ALS Advanced Launch System AT Aerojet TechSystems CTF Component Test Facility DAS Data Acquisition System FS1 Fire Switch 1 (One) GH2 Gaseous Hydrogen GPM Gallons per Minute GSE Ground Support Equipment ICD Interface Control Document LH2 Liquid Hydrogen MSFC Marshall . Liquid hydrogen is used in large volumes in the space program as a primary rocket fuel for combustion with oxygen or fluorine, and as a pro-pellent for nuclear powered rockets and space vehicles. Although used more commonly in the gaseous state, hydrogen is stored and transported as a liquid. Hydrogen File Size: KB. Space Shuttle Main Engine, Liquid Hydrogen Turbopump, and Alternate Turbopump Program. Center to Contact for More Information: Marshall Space Flight Center (MSFC) Implementation Method: I. Background: horsepower liquid hydrogen turbopump being flown on each flight of the Space Shuttle represents almost three decades of design. A development of the biof uel turbopump wa s initiated at the Institute of Aeronautics and Space (IAE) in under Brazilian Space Agency (AEB) support and in the context of the L75 Engine project.