Surface cooling of scramjet engine inlets using heat pipe, transpiration, and film cooling

Journal Article · Tue Sep 01 00:00:00 EDT 1992 · Journal of Thermophysics and Heat Transfer; (United States)

DOI:https://doi.org/10.2514/3.388· OSTI ID:7070158

Modlin, J M; Colwell, G T ^[1]

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1. U.S. Army, Strategic Defense Command, Huntsville, AL (United States) Georgia Institute of Technology, Atlanta (United States)

This article reports the results of applying a finite-difference-based computational technique to the problem of predicting the transient thermal behavior of a scramjet engine inlet exposed to a typical hypersonic flight aerodynamic surface heating environment, including type IV shock interference heating. The leading-edge cooling model utilized incorporates liquid metal heat pipe cooling with surface transpiration and film cooling. Results include transient structural temperature distributions, aerodynamic heat inputs, and surface coolant distributions. It seems that these cooling techniques may be used to hold maximum skin temperatures to near acceptable values during the severe aerodynamic and type IV shock interference heating effects expected on the leading edge of a hypersonic aerospace vehicle scramjet engine. 15 refs.

• OSTI ID: 7070158
• Journal Information: Journal of Thermophysics and Heat Transfer; (United States), Vol. 6:3; ISSN 0887-8722
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
INTAKE STRUCTURES
COOLING
TURBOJET ENGINES
AERODYNAMIC HEATING
COMPARATIVE EVALUATIONS
COMPUTERIZED SIMULATION
FILM COOLING
FINITE DIFFERENCE METHOD
HEAT PIPES
HYPERSONIC FLOW
LIQUID METALS
RESPONSE FUNCTIONS
TEMPERATURE DISTRIBUTION
ELEMENTS
ENGINES
EQUIPMENT
EVALUATION
FLUID FLOW
FLUIDS
FUNCTIONS
HEATING
ITERATIVE METHODS
LIQUIDS
MACHINERY
MECHANICAL STRUCTURES
METALS
NUMERICAL SOLUTION
SIMULATION
TURBOMACHINERY
330100* - Internal Combustion Engines