Fluid flow analysis of the SSME high pressure fuel and oxidizer turbine coolant systems

Cover of: Fluid flow analysis of the SSME high pressure fuel and oxidizer turbine coolant systems |

Published by Lockheed Missiles & Space Company, Inc., Huntsville Engineering Center in Huntsville, AL .

Written in English

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Subjects:

  • Engines -- Cooling.,
  • Space shuttles.

Edition Notes

Book details

Statementby G.A. Teal.
SeriesNASA-CR -- 183736., LMSC-HEC TR -- F 268780., NASA contractor report -- NASA CR-183736.
ContributionsHuntsville Engineering Center., United States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15286977M

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Fluid flow analysis of the SSME high pressure fuel and oxidizer turbine coolant systems The objective is to provide improved analysis capability for the Space Shuttle Main Engine (SSME) high pressure fuel and oxidizer turbine coolant systems. Each of the systems was analyzed to determine fluid flow rate and thermodynamic and transport properties at all key points in the systems.

Summary: The objective is to provide improved analysis capability for the Space Shuttle Main Engine (SSME) high pressure fuel and oxidizer turbine coolant systems.

Each of the systems was analyzed to determine fluid flow rate and thermodynamic and transport properties at all key points in the systems.

Get this from a library. Fluid flow analysis of the SSME high pressure fuel and oxidizer turbine coolant systems. [G A Teal; Huntsville Engineering Center.; United States. National Aeronautics and Space Administration.]. The objective is to provide improved analysis capability for the Space Shuttle Main Engine (SSME) high pressure fuel and oxidizer turbine coolant systems.

Each of the systems was analyzed to determine fluid flow rate and thermodynamic and transport properties at all key points in the : G. Teal. GET THIS BOOK The objective is to provide improved analysis capability for the Space Shuttle Main Engine (SSME) high pressure fuel and oxidizer turbine coolant systems.

Each of the systems was analyzed to determine fluid flow rate and thermodynamic and transport properties at all key points in the systems.4/5(21). Unsteady computational fluid dynamics (CFD) analyses of the SSME alternate turbopump development (ATD) high pressure fuel turbopump (HPFTP) and high pressure oxidizer turbopump (HPOTP) turbine first stage blades are presented.

Velocity and pressure characteristics of a model SSME high pressure fuel turbopump Under the present effort an experiment rig has been constructed, an instrumentation package developed and a series of mean and rms velocity and pressure measurements made in a turbopump which modelled the first stage of the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump.

The from the fuel and oxidizer preburners drives the high-pressure pump turbines, then flows through the main injector, where it burns with oxi­ dizer and additional coolant fuel.

Engine Arrangement Figure 6 shows a cutaway view of the preburners, high-pressure turbopumps, hot-gas manifold, and main combustion chamber. Fluid flow analysis of the SSME high pressure fuel and oxidizer turbine coolant systems high pressure fuel and oxidizer turbine coolant systems. Each of the systems.

This banner text can have markup. web; books; video; audio; software; images; Toggle navigation. Anderson, P.

et al, "Fluid Flow Analysis of the SSME High Pressure Oxidizer Turbopump Operating at Full Power Level", Lockheed Missiles & Space Company, Inc. For example, an engine balance program balances the pressure drops in the fuel, oxidizer, and pressurizing gas flow systems; similar programs balance the pump and turbine power, speeds, and torques (see Section ), compare different TP configurations (see Section ); some balance programs also calculate approximate masses for engine.

The nozzles of Space Shuttle Columbia's three RSs following the landing of STS The engine's nozzle is in (Template:Convert/round m) long with a diameter of in (Template:Convert/round m) at its throat and in (Template:Convert/round m) at its exit.

The nozzle is a bell-shaped extension bolted to the main combustion chamber, referred to as a de Laval nozzle. 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 cold air test program was completed on the SSME (Space Shuttle Main Engine) HPFTP (High-Pressure Fuel Turbopump) turbine with production nozzle vane rings and polished coated rotor blades with a smooth surface finish of 30[mu]in. ( [mu]m) rms (root mean square). Find the most up-to-date version of NASA-LLIS at Engineering @article{osti_, title = {Space shuttle main engine high pressure fuel turbopump turbine blade cracking}, author = {Lee, H}, abstractNote = {The analytical results from two-dimensional (2D) and three-dimensional (3D) finite element model investigations into the cracking of Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP) first- and second-stage turbine blades are.

All of the fuel is then burned with part of the oxidizer in a high-pressure precombustor. The combustion products provide high-energy gas to drive the engine pump turbines. The total exhaust flow from the turbine is then injected into the main combustion chamber, where it burns with the remaining oxidizer.

This paper presents an accurate analysis of thermal and fluid distributions for turbine cooled vanes and blades using the commercial CFD software FLUENT.

Investigations consisted of five tasks. Task 1 investigated static pressure (Mach number) and heat transfer coefficient for. 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. Aerodynamic Aspects of the Sealing of Gas-Turbine Rotor–Stator Systems, Part 2: The Performance of Simple Seals in a Quasi-Axisymmetric External Flow Int.

Heat Fluid Flow, Vol. If steam is extracted from the turbine at a pressure of psia, energy/mass balance calculations show that the flow rate to the heater should be percent of the total steam flow.

The. Analysis of the Space Shuttle Main Engine. Introduction. The Space Shuttle Main Engine (SSME) is a high performance liquid rocket engine that is fueled with liquid hydrogen and uses liquid oxygen as an oxidizer.

It was the first large scale reusable liquid rocket, and can deliver an incredible MN of thrust at maximum operating power. The invention is a coolant system for a rocket engine.

The rocket engine includes an injector, a fuel supply, an oxidizer supply, a pump for feeding fuel from the fuel supply to the injector, a pump for feeding oxidizer from the oxidizer supply to the injector, a combustor, and a nozzle, the combustor and nozzle forming a combustor and nozzle assembly.

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. Rocket engines produce thrust by the expulsion of an exhaust fluid that has been accelerated to high speed through a propelling fluid is usually a gas created by high pressure (to-4,pound-per-square-inch (10 to bar)) combustion of solid or liquid propellants, consisting of fuel and oxidiser components, within a combustion chamber.

Fuel-rich GG combustion (~3% of total propellant flow) Moderate pump and turbine Pc, lower performance) Oxidizer Pump Turbine Fuel Pump Oxidizer Fuel Exhaust Gas generator Thrust chamber No secondary flow losses (turbine exhausts to thrust chamber) Preburner (% LOX flow, ~4% fuel flow) – no coking High pump and turbine speeds.

An internal combustion engine (ICE) is a heat engine in which the combustion of a fuel occurs with an oxidizer (usually air) in a combustion chamber that is an integral part of the working fluid flow circuit.

In an internal combustion engine, the expansion of the high-temperature and high-pressure gases produced by combustion applies direct force to some component of the engine. The design and installation at the Naval Postgraduate School of a cold-flow test facility for the turbine of the high-pressure fuel turbopump of the Space Shuttle Main Engine, is reported.

The specific article to be tested is the 'Alternate Development Model' designed and manufactured by Pratt & Whitney. design of an oxygen turbopump for a dual expander cycle. 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 LPOTP then being. These changes included applying surface texture to important parts of the fuel turbine blades to improve the material properties in the pressure of hydrogen and incorporating a damper into the high-pressure oxidizer turbine blades to reduce vibration.

Main combustion chamber life has been increased by plating a welded outlet manifold with nickel. Reaction Turbine: Kaplan Turbine (used for low head, high discharge installations) Degree of Reaction (DR) is the ratio of static pressure drop (pressure energy converted) in the rotor to the total pressure drop (total hydraulic energy available) in the turbine.

[DR turbine and DR> indicates a reaction turbine]. In this study, the performance of regenerative cooling system for large expansion ratio rocket engines (A e /A t ∼ ) is investigated numerically. During combustion and gas expansion, the walls of the combustion chamber and the rocket nozzle are exposed to high temperature gas (∼ K), which can ultimately lead to structural failure.

Flow is still from high to low pressure. As the fluid flows out of the venturi, its velocity decreases and pressure increases (Bernoulli principle). This time however, there is a pressure differential across the venturi.

That is, the pressure on the 'inlet' side is higher than the pressure on the 'outlet' side, so flow is still from high. Space Shuttle Main Engine Propellant Flow The Space Shuttle Main Engine used a two-stage combustion process. High-pressure Fuel Turbopump Main Fuel Valve Chamber Coolant Valve Valve Main Injector Main Combustion Chamber Nozzle Fuel Preburner Powerhead Oxidizer Valve Low-pressure Oxidizer Turbopump High-pressure Oxidizer Turbopump Oxygen.

STS On Aug the first launch attempt of STS was aborted at T-3 seconds because of a disagreement in the turbine fuel flow sensors of Space Shuttle Main Engine (SSME) 2.

At seconds after ignition SSME 2 experienced a failure of the fuel flow meter channel A2 speed pickup coil sensor (loss of redundancy) to respond to the. Fluid temperature changes calculated.

FluidFlow is provided with a database of thermal conductivity values for pipe materials, coatings, insulation and soil types. You can also add new data. Track changes in fluid phase state arising from heat transfer. Buried pipe heat transfer. A lot of technology in the high pressure pumps, both fuel and oxidizer.

The main problem with the high pressure fuel pump was sub-synchronous whirl, and I'll say a little bit more about this in a moment. It was a very traumatic time in the early period of developing the Shuttle main engine.

It caused a lot of delays. A tough problem to solve. Flow of Fluids v16 simulates the operation of small piping systems transporting liquids and industrial gases under a variety of expected operating conditions. Training / Learning Providing top-notch training courses to keep engineers, plant operators and maintenance personnel up-to-date on the most recent engineering standards and best practices.

There the fuel and oxidizer each branch out into three parallel paths, to each engine. In each branch, prevalves must be opened to permit flow to the low-pressure fuel or oxidizer turbopump.

[edit] Oxidizer system. Major components of the Space Shuttle main engineThe Low Pressure Oxidizer Turbopump (LPOTP) is an axial-flow pump driven by a six. The three oxidizer valves sequence the main events during the crucial first two seconds of start. The fuel preburner oxidizer valve (FPOV) is ramped to 56% to provide LOX for ignition in the fuel preburner (FPB) in order to provide initial turbine torque of the high-pressure fuel.

The threshold parameter depends on the specific thermodynamic conditions of the coolant and in particular on its pressure level. In the present study, a parametric numerical analysis has been carried out on the flow of supercritical methane in heated channels, for an assigned inlet temperature level and varying the inlet pressure.

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