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2 edition of Laser doppler velocimetry in the space-shuttle main engine high-pressure fuel turbopump found in the catalog.

Laser doppler velocimetry in the space-shuttle main engine high-pressure fuel turbopump

by James D. Southward

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Published by Naval Postgraduate School, Available from National Technical Information Service in Monterey, Calif, Springfield, Va .
Written in English


About the Edition

Modifications were made to the Naval Postgraduate School cold-flow turbine test rig to enable integration of a two-component laser-doppler velocimetry (LDV) system. The test turbine was the Space-Shuttle Main Engine, High-Pressure Fuel Turbopump, Alternate-Turbopump Development Model, manufactured by Pratt & Whitney. Flow field measurements were obtained, using a the LDV system, in the first-stage rotor end-wall region of the test turbine, at three axial locations and at three depths from the end wall. For each survey location, velocity ratios, absolute flow angle, turbulence intensities, and correlation coefficients were examined. The laser data exhibited distinct trends with axial position, depth from the end wall, and with circumferential position. In addition to the laser data, velocity profiles were determined at the first- stage stator inlet and rotor exit planes, using a three-hole pressure probe. Both laser and probe data were taken at referred rotational speeds in the range 4815 to 4853 rpm. Phase-locked measurements were recorded using a once-per- revolution signal from a magnetic pick-up as a trigger. TSI Phase-resolved software version 2.06 was used for laser data acquisition and reduction.

Edition Notes

StatementJames D. Southward
The Physical Object
Paginationxxi, 149 p. ;
Number of Pages149
ID Numbers
Open LibraryOL25182563M

Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats.   The schematic diagrams of Fig. show each cycle with a separate turbopump for fuel and for oxidier. However, an arrangement with the fuel and oxdizer pump driven by the same turbine is also feasible and sometimes reduces the hardware mass, volume, and cost/5.

Liquid Rocket Engine Turbopump Bearings, NASA SPACE VEHICLE DESIGN CRITERIA (Chemical Propulsion), NASA SP, NASA (Washington, DC, United States), NASA Lewis Research Center (Cleveland, OH, United States), March , pp. 85, (71N).   PDF; PDF; Print; Help NASA SBIR/STTR Program Support For questions about the NASA SBIR/STTR solicitations, the proposal preparation and electronic submission process, and other program related areas, please contact the NASA SBIR/STTR Program Support Office. Phone: Email: [email protected] NASA SBIR/STTR Program Support is available Monday .

Created Date: 10/3/ PM. Close Drawer Menu Close Drawer Menu Menu. Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of .


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Laser doppler velocimetry in the space-shuttle main engine high-pressure fuel turbopump by James D. Southward Download PDF EPUB FB2

The test turbine was the Space-Shuttle Main Engine, High-Pressure Fuel Turbopump, Alternate-Turbopump Development Model, manufactured by Pratt & Whitney.

Flow field measurements were obtained, using a the LDV system, in the first-stage rotor end-wall region of the test turbine, at three axial locations and at three depths from the end : James D.

Southward. Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection Laser doppler velocimetry in the space-shuttle main engine high-pressure fuel turbopump. Modifications were made to the Naval Postgraduate School cold-flow turbine test rig to enable integration of a two-component laser-doppler velocimetry (LDV) system.

The test turbine was the Space-Shuttle Main Engine, High-Pressure Fuel Turbopump, Alternate-Turbopump Development Model, manufactured by Pratt & : The Space Shuttle Main Engine (SSME) was designed for 55 missions.

The engines were generally referred to as the center (engine 1), left (engine 2), and The last block upgrade was Block II, which added a new high-pressure fuel turbopump. Block II first flew on STS The cumulative effects.

The RS engine consists of various pumps, valves, and other components which work in concert to produce thrust. Fuel (liquid hydrogen) and oxidizer (liquid oxygen) from the Space Shuttle's external tank entered the orbiter at the umbilical disconnect valves and from there flowed through the orbiter's main propulsion system (MPS) feed lines; whereas in the Space Launch System (SLS), fuel and Associated L/V: Space Shuttle, Space Launch System.

The main shaft of the turbopump rotates at 37, rpm—a car operating at 60 mph runs at 2, rpm. One Space Shuttle Main Engine generates enough thrust to maintain the flight of Boeing s.

Even though a Space Shuttle Main Engine weighs one-seventh as much as a locomotive engine, its high-pressure fuel pump alone delivers as muchFile Size: KB. The Space Shuttle is propelled into orbit by two solid rocket motors and three liquid fed main engines.

After the solid motors fall away, the shuttle engines continue to runfor a total time of 8 minutes. These engines are fed propellants by low and high pressure turbopumps.

A critical partof the turbopump is theFile Size: 5MB. 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. MAIN PROPULSION SYSTEM The main propulsion system, assisted by the two solid rocket boosters during the initial phases of the ascent trajectory, provides the velocity increment from lift-off to a predetermined velocity increment before orbit two SRBs are jettisoned after their fuel has been expended, but the MPS continues to thrust until the predetermined velocity is achieved.

The space shuttle main engine (SSME) is a high-performance liquid propellant rocket engine producing kN of thrust at full power level. It uses four turbopumps, two high pressure, and two low pressure. The two high-pressure pumps are driven by gas turbines powered by hydrogen-rich steam provided by individual by: 6.

The design relies on putting pumps in series to achieve the necessary pressures and fluid flow rates through system. And, the SSME has not one but two separate preburners, one for the high pressure fuel turbopump and one for the high pressure oxidizer turbopump. It’s a very complex engine, but it has extraordinary capabilities.

The actual engine is significantly more complicated than this (even in a simplified schematic), but this is the basic premise of any turbopump-fed engine: hot gas turns a turbopump that pumps up the main propellant supply and injects it into the combustion chamber.

The Space Shuttle Main Engine (SSME) is basically comprised of a combustion chamber and nozzle, high and low pressure oxygen turbopumps and high and low pressure fuel turbopumps.

In the current configuration, the high pressure fuel (HPTFP) and high pressure oxygen turbopumps (HPOTP) have experienced a history of ball bearing wear.

Shown here is a cutaway model of the liquid hydrogen fuel pump for the space shuttle main engine (SSME). During tests in the s, it ran to a pressure of 5, pounds per square inch. Unlike all prior, single-use liquid-propellant rocket engines, the SSME featured reusable interchangeable parts.

The Space Shuttle Main Engines was the only high-pressure closed-cycle reusable cryogenic rocket engine ever flown. Three of these engines were mounted in the base of the American space shuttle, and were fed liquid hydrogen and liquid oxygen propellants.

ENGINE CONTROLS, CALIBRATION, INTEGRATION, AND OPTIMIZATION In this chapter we first discuss a complex high-precision, high-speed, rotating Space Shuttle Main Engine ~ Modified Staged Combustion Cycle HPFTP, high-pressure fuel turbopump.

dBoost impeller stage for oxygen flow to preburners or gas generator. TURBOPUMPS, ENGINE DESIGN File Size: KB. The first overhauled Space Shuttle Main Engine (SSME) high-pressure liquid oxidizer (LOX) turbopump, which flew on six space shuttle flights.

A 'read' is counted each time someone views a publication summary (such as the title, abstract, and list of authors), clicks on a figure, or views or downloads the full-text. Laser-Doppler-Velocimetry measurements were carried out in order to record rotor phase resolved velocity, flow angle and turbulence distributions upstream and downstream of the second vane row at.

Chapter III: The Accident [19] Flight of the Space Shuttle Challenger on Mission L began at a.m. Eastern Standard Time on Janu It ended 73 seconds later in an explosive burn of hydrogen and oxygen propellants that destroyed the External Tank and exposed the Orbiter to severe aerodynamic loads that caused complete structural breakup.

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 .(MPa), and it is piped to a heat exchanger on the rocket engine nozzle where it is heated to °K. To heat the he lium to K will require approximately % of the heat energy of a rocket engine which runs at psi ( MPa).

Large, high -pressure engines may require that the helium be heated by combustion of the propellants. Each of the space shuttle's main engines is fed liquid hydrogen by a high-pressure pump. Turbine blades inside the pump rotate at rev/s. A point on one of the blades traces out a circle with a radius of m as the blade rotates.

(a) What is the magnitude of the centripetal acceleration that the blade must sustain at this point? (b) Express this acceleration as a multiple of g=m/s2.