Impact of air-breathing propulsion system developments on test facilities.

The aspirated hypersonic air-breathing propulsion system requires a large amount of power generation, but its special structure makes it impossible to adopt common power generation methods. The high-temperature gaseous hydrocarbon fuel thermal power generation (TPG) system was developed to solve the power generation problem for hypersonic air-breathing propulsion system. But off-design operating conditions of the hypersonic propulsion system results in a more complex process for both propulsion system and the TPG system. To better analyzing the dynamic thermos-physical characteristics of hypersonic airbreathing propulsion system considering thermal-mechanical coupling process among cooling/TPG system, a dynamic analytical model was developed, and the dynamic thermos-physical characteristics of TPG system under different off-design working conditions were conducted. It can be concluded from the analytical results that the dynamic process of thermos-physical characteristics shows a complex trend under the flight Mach number and fuel equivalence ratio off-design working conditions. Such complexity of dynamic characteristics brings difficulties in fuel supply for the propulsion system.

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Near-optimal propulsion system operation for air-breathing launch vehicles

10.2514/6.1994-3635 ◽

1994 ◽

Cited By ~ 1

Author(s):

M. Ardema ◽

J. Bowles

Keyword(s):

Propulsion System ◽

Launch Vehicles ◽

System Operation ◽

Air Breathing

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Response of an Operational Turbofan Engine to a Simulated Nuclear Blast

Journal of Fluids Engineering ◽

10.1115/1.3242631 ◽

1987 ◽

Vol 109 (2) ◽

pp. 121-129 ◽

Cited By ~ 1

Author(s):

M. G. Dunn ◽

C. Padova ◽

R. M. Adams

Keyword(s):

Shock Waves ◽

Transient Response ◽

Incident Shock ◽

Blast Waves ◽

Propulsion System ◽

Maximum Speed ◽

Turbofan Engine ◽

Air Breathing ◽

Ludwieg Tube ◽

Yaw Angle

This paper describes the results of a measurement program designed to determine the transient response of an air-breathing propulsion system to simulated nuclear blast waves. A Ludwieg-tube facility, incorporating a driver technique consisting of an activating chamber and a nonfrangible diaphragm, was used to create the required shock waves. Detailed measurements were performed at incident shock overpressures of approximately 6.9, 10.3, 13.8, and 17.2 kPa (1.0, 1.5, 2.0, and 2.5 psi). For each of these overpressures, data were obtained for engine speeds of 0, 80, 90, and 100 percent of maximum speed. Typical results are presented for distortion patterns at the fan face for both an extended bellmouth and a S-shaped inlet at either 0 or 20 deg yaw angle.

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