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Saturday, August 8, 2020 | History

3 edition of High pressure oxidizer turbopump (HPTOP) inducer dynamic design environment found in the catalog.

High pressure oxidizer turbopump (HPTOP) inducer dynamic design environment

High pressure oxidizer turbopump (HPTOP) inducer dynamic design environment

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  • 14 Currently reading

Published by National Aeronautics and Space Administration, Marshall Space Flight Center, National Technical Information Service, distributor in MSFC, Ala, [Springfield, Va .
Written in English

    Subjects:
  • Engine design.,
  • High pressure.,
  • Impellers.,
  • Oxidizers.,
  • Space shuttle main engine.,
  • Strain measurement.,
  • Turbine pumps.

  • Edition Notes

    StatementD.A. Herda, R.S. Gross.
    SeriesNASA technical paper -- 3589.
    ContributionsGross, R. S., George C. Marshall Space Flight Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15426077M

    Next, wishing to express yourself, you can address the age-old issue of the intermediate seal in the oxidizer turbopump. Take a good look at the first two schematics presented here. You will see that the oxidizer pump is being driven by a turbine using fuel as a working fluid. Get this from a library! An SSME high pressure oxidizer turbopump diagnostic system using G2tm real-time expert system. [Ten-Hui Guo; United States. National Aeronautics and Space Administration.].

    How is High Pressure Oxidizer Turbopump (US NASA) abbreviated? HPOT stands for High Pressure Oxidizer Turbopump (US NASA). HPOT is defined as High Pressure Oxidizer Turbopump (US NASA) frequently. The main oxidizer valve (MOV) was a butterfly-type valve, spring-loaded to the closed position, pneumatically operated to the open position, and pneumatically assisted to the closed position. It was mounted between the oxidizer high-pressure duct from the oxidizer turbopump and the oxidizer inlet on the thrust chamber assembly.

    This auction is for a NASA Space Shuttle main engine acrylic display. The display has a High Pressure Oxidizer Turbopump Turbine Blade embedded in it that was flown in space on missions: STS, STS-3 from testing of the IPD Oxidizer Turbopump (OTP) ensued at E-1 Cell 3. For the hot-fire OTP test series, the IPD Workhorse Preburner was mated to the IPD OTP. Liquid oxygen (LOX) and GH2 were supplied at high pressure to the preburner and the resulting high-pressure, high-temperature combustion gases were directed into the turbine side of the IPD OTP.


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High pressure oxidizer turbopump (HPTOP) inducer dynamic design environment Download PDF EPUB FB2

Oxidizer system. The low-pressure oxidizer turbopump (LPOTP) is an axial-flow pump which operates at approximately 5, rpm driven by a six-stage turbine powered by high-pressure liquid oxygen from the high-pressure oxidizer turbopump (HPOTP).

It boosts the liquid oxygen's pressure from to MPa ( to psi), with the flow from the Associated L/V: Space Shuttle, Space Launch System. Get this from a library.

High pressure oxidizer turbopump (HPTOP) inducer dynamic design environment. [David A Herda; R S Gross; George C. Marshall Space Flight Center.]. The main oxidizer valve (MOV) was a butterfly-type valve, spring-loaded to the closed position, pneumatically operated to the open position, and pneumatically assisted to the closed position.

It was mounted between the oxidizer high-pressure duct from the oxidizer turbopump and the oxidizer inlet on the thrust chamber y of origin: United States. We've got 2 shorthands for High Pressure Oxidizer Turbopump» What is the abbreviation for High Pressure Oxidizer Turbopump. Looking for the shorthand of High Pressure Oxidizer Turbopump?This page is about the various possible meanings of the acronym, abbreviation, shorthand or slang term: High Pressure Oxidizer Turbopump.

image/svg+xml Low-pressure fuel turbopump Fuel inlet GH2 pressure outlet to external tank Fuel preburner OX valve Hot-gas manifold Main injector Main oxidizer valve GO2 pressurant outlet to external tank Fuel preburner injector Fuel preburner High-pressure fuel turbopump Main combustion chamber Fuel Oxidant Hot gases Combustion zone High-pressure oxidizer turbopump Legend Oxidizer heat.

An illustration of an open book. Books. An illustration of two cells of a film strip. Video. An illustration of an audio speaker. Audio An illustration of a " floppy disk. (NTRS) Effect of flange bolt preload on Space Shuttle main engine high pressure oxidizer turbopump housing analysis Item.

An experimental study on a rotating-shaft seal system for a high-pressure liquid oxygen (LOX) turbopump has been conducted to develop the LE-7 engine for the Japanese H-II launch vehicle.

The LOX turbopump rotating-shaft seal system, which prevents LOX ( MPa) and the high-pressure turbine-drive gas ( MPa, K) from mixing during high-speed operations (18, to 20. At all other conditions, excess gaseous and liquid oxygen are recirculated to the the low-pressure oxidizer turbopump inlet through the engine oxidizer bleed duct.

The pogo accumulator is charged (pressurized) at engine shutdown to provide a positive pressure at the HPOT inlet, which prevents HPOT overspeed in the zero-gravity environment.

The low pressure fuel turbopump and low pressure oxidizer turbopump receive the propellants at low NPSP and raise their pressures sufficiently to optimize the high pressure fuel and oxidizer turbopumps at high speed. The added complexity of four turbopumps is justified to optimize the turbomachinery weight and maintain suction performance.

functions. These functions included “the high-pressure oxidizer turbopump intermediate seal cavity and preburner oxidizer dome purge, pogo system postcharge, and pneumatic shutdown.” Thrust Vector Control Actuators Two main engine TVC actuators were connected to the powerhead of each SSME.

One was for yaw and the other for pitch. High Pressure Oxidizer Turbopump. Governmental» NASA. Add to My List Edit this Entry Rate it: ( / 0 votes) Translation Find a translation for High Pressure Oxidizer Turbopump in other languages: Select another language: Select - 简体中文 (Chinese - Simplified).

High Pressure Oxidizer Turbopump Housing Analysis 7. Author(s) J.B. Min, L.M. Johnston, and B. Czekalski* 9. Performing Organization Name and Address George C. Marshall Space Flight Center Marshall Space Flight Center, Alabama Sponsoring Agency Name and Address National Aeronautics and Space Administration Washington, DC May A schematic of the High Pressure Oxidizer Turbopump (HPOTP) seal system on the Space Shuttle Main Engine (SSME) is shown in Figure 1.

Generally, its purpose is to prevent the leakage of any fluids in down the shaft and in particular, to prevent the mixing of hot Hydrogen rich turbine gases. These analyses were undertaken to aid in the understanding of flow phenomena in the Alternate Turbopump Development (ATD) High-pressure Oxidizer Turbopump.

This paper presents the test results from the Space Shuttle Main Engine (SSME) instrumented High Pressure Oxidizer Turbopump (HPOTP). The turbopump was tested on Enginea highly instrumented engine, in an effort to characterize the turbopump and the engine system.

Seven tests, for a total duration of seconds, were performed over a five month time period. Cracking of space shuttle main engine (SSME) high-pressure oxidizer turbopump (HPOTP) knife-edge seals (KES) has been observed in several units. Although this cracking has not resulted in the complete fracture of any units, the consequences of such a fracture could be severe.

As a result, life limits have been imposed that effectively. Two turbomachines in the oxidizer side: the low-pressure oxidizer turbopump (LPOTP) and the high-pressure oxidizer turbopump (HPOTP) (LPFTP) and the high-pressure fuel turbopump (HPFTP) The main advantage of the low-pressure turbopumps is that they boost the liquid oxygen and hydrogen from low pressure to the high-pressure turbopumps.

A turbopump is a propellant pump that comprises basically two main components: a rotodynamic pump and a driving gas turbine, usually both mounted on the same shaft, or sometimes geared together.

The purpose of a turbopump is to produce a high pressure fluid for feeding a combustion chamber or other use. A turbopump can comprise one of two types of pumps: centrifugal pump, where the pumping is.

A fiberoptic deflectometer is under development to diagnose bearing degradation of the turbine end bearings of the space shuttle main engine (SSME) high pressure oxidizer turbopump (HPOTP). The deflectometer, which measures bearing outer race deformations, provides better diagnostic sensitivity tha.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA. HPOTP High-Pressure Oxidizer Turbopump HPV Helium Precharge Valve IE Input Electronics LH Left Hand LH 2 Liquid Hydrogen LO 2 Liquid Oxygen LOX Liquid Oxygen LPF Low-Pressure Fuel LPFTP Low-Pressure Fuel Turbopump LPO Low-Pressure Oxidizer LPOTP Low-Pressure Oxidizer Turbopump LRU Line Replaceable Unit.

The flow from the LPOT is supplied to the high-pressure oxidizer turbopump. During engine operation, the pressure boost permits the HPOT to operate at high speeds without cavitating. The LPOT operates at approximately 5, rpm.

The LPOT, which is approximately 18 by 18 inches, is connected to the vehicle propellant ducting and supported in a.HPOP stands for High Pressure Oxidizer Pump (US NASA).

HPOP is defined as High Pressure Oxidizer Pump (US NASA) somewhat frequently. Printer friendly. Menu Search. New search features Acronym Blog Free (book) Harry Potter and the Order of the Phoenix High Pressure Oxidizer Turbopump (US NASA) High Pressure Oxidizer Turbopump (SSME.