Last edited by Duhn
Sunday, July 19, 2020 | History

3 edition of Thermal and structural analysis of a hollow core Space Shuttle Main Engine (SSME) turbine blade found in the catalog.

Thermal and structural analysis of a hollow core Space Shuttle Main Engine (SSME) turbine blade

Thermal and structural analysis of a hollow core Space Shuttle Main Engine (SSME) turbine blade

  • 217 Want to read
  • 40 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Crystal structure.,
  • Finite element method.,
  • Heat resistant alloys.,
  • Heat transfer.,
  • Nickel alloys.,
  • Single crystals.,
  • Space Shuttle main engine.,
  • Stress distribution.,
  • Structural analysis.,
  • Turbine blades.,
  • Turbine pumps.

  • Edition Notes

    StatementAli Abdul-Aziz and Sreeramesh Kalluri, Michael A. McGaw.
    SeriesNASA technical memorandum -- 107089.
    ContributionsKalluri, Sreeramesh., McGaw, Michael A., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15424037M

    @article{osti_, title = {Thermal hydraulic design analysis of ternary carbide fueled square-lattice honeycomb nuclear rocket engine}, author = {Furman, Eric M and Anghaie, Samim}, abstractNote = {A computational analysis is conducted to determine the optimum thermal-hydraulic design parameters for a square-lattice honeycomb nuclear rocket engine core that will incorporate ternary. The first Space Shuttle didn't reach orbit until , but NASA was working on designs for nearly a dozen years before that. And looking at the progression of these concept drawings, you can.

    Space Shuttle Thermal Protection System 8 New Requirements 1. Maintain higher amount of structural integrity 2. Tile condition must be easily monitored during a mission 3. TPS must have on-orbit repair capabilities 4. Reduced maintenance to reduce costs. A thermal insulating structure for providing thermal insulation, structural load accommodations, and noise attenuation for surfaces in aerospace systems that are exposed to high temperatures. At the side adjacent the structure to be protected is a high-temperature solid back sheet to which is adhesively bonded a honeycomb core having a perforated buried septum.

    The aim of this research was to evaluate the effectiveness of phase-change materials (PCMs) incorporated into the supply air duct of a hollow-core slab ventilation system. Both experimental and numerical approaches were adopted in this investigation. In the experimental work, the air was passed through a PCM-incorporated aluminum air duct, and the temperature at various points of the duct was. The Buran orbital vehicle programme was developed in response to the U.S. Space Shuttle programme, which in the s raised considerable concerns among the Soviet military and especially Defense Minister Dmitry authoritative chronicler of the Soviet and later Russian space programmes, the academic Boris Chertok, recounts how the programme came into being.


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Thermal and structural analysis of a hollow core Space Shuttle Main Engine (SSME) turbine blade Download PDF EPUB FB2

Full text of "NASA Technical Reports Server (NTRS) Thermal and Structural Analysis of a Hollow Core Space Shuttle Main Engine (SSME) Turbine Blade" See other formats NAS A Technical Memorandum £ Mb 7 IcHi sj^s' Thermal and Structural Analysis of a Hollow Core Space Shuttle Main Engine (SSME) Turbine Blade Ali Abdul- Aziz and Sreeramesh Kalluri NYMA, Inc.

Thermal and structural analysis of a hollow core Space Shuttle Main Engine (SSME) turbine blade Article (PDF Available) January with Reads How we measure 'reads'. Get this from a library. Thermal and structural analysis of a hollow core Space Shuttle Main Engine (SSME) turbine blade.

[Ali Abdul-Aziz; Sreeramesh Kalluri; Michael A McGaw; United States. National Aeronautics and Space Administration.]. Thermal and Structural Analysis Conducted on Hollow-Core Turbine Blade of the Space Shuttle Main Engine.

Abstract. Hot-section components of spacecraft engines are exposed to severe thermal-structural loading conditions, especially during the startup and shutdown portions of the engine cycle.

Thermal and Structural Analysis Conducted on Hollow-Core Turbine Blade of the Space Shuttle Main Engine Hot-section components of spacecraft engines are exposed to severe thermal-structural loading conditions, especially during the startup and shutdown portions of the engine cycle.

Thermal Finite-Element Analysis of Space Shuttle Main Engine Turbine Blade Article (PDF Available) in Finite Elements in Analysis and Design 5(4) October with 58 Reads How we measure. The space shuttle Challenger (STS) exploded just over one minute after take-off on 28 Januarykilling seven astronauts.

After an exhaustive investigation by NASA and other US agencies the cause of the accident was found. The space shuttle is fitted with two solid rocket boosters that generate an extraordinary amount of thrust during take-off that launches the main vehicle into space.

The Space Shuttle Main Engine is a staged combustion cycle engine that burns a mixture of gaseous hydrogen and liquid oxygen.

The identifying feature of a staged combustion engine is that most of the fuel flow (except for a small coolant flow) and a small amount of the oxidizer flow are “preburned” in a preburner at an extremely fuel-rich.

The Space Shuttle Main Engine* (SSME) is a reusable, high-performance rocket engine being developed to satisfy the performance, life, reliability, and operational requirements of the Space Shuttle Qrbi- ter. The design includes simple, low-cost mainte­ nance features resulting from a viable maintaina­.

classical structural design would have the doors provide strength when the fuselage encountered loads from bending, twisting, shear, internal pressure, and thermal gradients. The doors also had to open in space to provide access to the payload and enable the radiators to radiate heat to space.

Equally important, the doors had. 38 Solar-Thermal Engine. Alternate Names: Type: For example, the Space Shuttle Main Engines, of which the Space Shuttle Orbiter used three, each had a power of GW. The Hydrogen flow is seeded with an absorbent material to directly absorb the thermal radiation from the core.

The core is kept from leaking out the nozzle either by a. Full text of "NASA Technical Reports Server (NTRS) Assessment of Technologies for the Space Shuttle External Tank Thermal Protection System and Recommendations for Technology 2; Structural Analysis Technologies and Modeling Practices" See other formats NASA/TM Assessment of Technologies for the Space Shuttle External Tank Thermal.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Aerodynamics []. US Air Force Stability and Control Data Compendium - Starting in the 's, the US Air Force collected data for predicting the aerodynamic behavior of aircraft.

This link is to the text version of the compiled data, known as the USAF DATCOM, which is a page, then, versions of the data and formulas have been compiled into software modules. Thermal analysis such as differential scanning calorimetry, thermogravimetric analysis, thermomechanical analysis, and differential thermal analysis can establish the bases for a proper and comprehensive evaluation of the thermal response of composite TPS materials when exposed to high temperatures, enabling the modeling of the ablation process.

space shutl'le main engine structural analysis and data reduction/evaluation volume high pressure fuel turbo-pump preburner pump bearing assembly analysis april contract nas prepared for 0 u 5 oa nu 06 national aeronautics and space administration george c.

marshall space flight center, al 0 ct dc] bn by gloria b. power. The background to the shuttle’s tiles lay in work dating to the early s at Lockheed Missiles & Space Company.

A Lockheed patent disclosure provided the first description of a reusable insulation made of ceramic fibers for use as a re-entry vehicle heat shield. In other phased shuttle Thermal Protection System development efforts. space shuttle main engine workshop.

solid rocket booster processing. hypergolic maintenance and checkout facility. orbiter mating. space shuttle vehicle testing.

mobile launcher platform. crawler-transporter. launch complexes a and b. fixed service structure. rotating service structure. sound suppression water system.

The Shuttle Reference Manual, most recently revised inis an indepth technical guide to space shuttle equipment and operations. It was accurate in and while most of the information provided here from the manual is still accurate today, some facts may be outdated. The engine illustrated is similar to the Space Shuttle main engine, with a specific impulse of seconds.

The De Laval nozzle has a area ratio, and is regeneratively-cooled with liquid hydrogen. The chamber temperature is K, and the chamber pressure is MPa. hollow-core slabs [6,7]. Winwood et al. [8] performed a three-dimensional (3D) Computational Fluid Dynamics (CFD) analysis of a hollow-core slab in PHONICS using a simplified geometry.

The effects of various parameters (e.g., insulation on the surface, a variation of thermal conductivity of the slab.The Space Shuttle Main Engine (SSME) (Figure 1) is a high chamber pressure (over 3, pounds per square inch) rocket engine that burns liquid oxygen (LOX) and liquid hydrogen (LH2) at a mixture ratio of 6 pounds of LOX for every pound of LH2.

It produces a rated thrust ofpounds (vacuum).All space vehicles of recent origin have several composite structural systems. CFRP is the obvious choice because of its excellent thermo-mechanical properties, i.e., high specific stiffness and strength, higher thermal conductivity and lower coefficient of thermal expansion.

The future large space stations are likely to be built with CFRP.