The Use of Stream Thrust Concepts for the Approximate Evaluation of Hypersonic Ramjet Engine Performance

Curran, E. T.; Craig, R. R.

doi:10.21236/ad0769481

Cited by 31 publications

(14 citation statements)

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“…The approach given in equations 1 and 3 are the primary tools with which the impact of technology concepts will be evaluated in this paper ¶ . 19…”

Section: Second Law Methodsmentioning

confidence: 99%

“…The HSCT was selected for ¶ Note that exergy and gas horsepower are not the only second law concepts with potential application to gas turbine engines. Specifically, the concepts of stream thrust analysis 19 , thrust work potential 14 , and the lost thrust method 14 have the potential to be useful metrics of propulsion system performance.…”

Section: Case Study: High Speed Civil Transportmentioning

confidence: 99%

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Analysis of advanced technology impact on HSCT engine cycle performance

Roth

Mavris

1999

35th Joint Propulsion Conference and Exhibit

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The objective of this paper is to describe and apply methods that could assist the propulsion system designer in the evaluation and selection of propulsion technologies. The focus here is on the aerothermodynamic aspects of the problem, particularly estimation of engine internal losses. This is accomplished by leveraging developments in second law analysis methods that are able to quantify the theoretical work potential as well as the loss in work potential. Two basic methods, exergy and "gas horsepower," are described and the suitability of each for propulsion systems analysis is discussed. These are used to develop a simple approach to engine internal loss estimation, and are then demonstrated on several basic technology scenarios for a High Speed Civil Transport Propulsion System. The various sources of loss for each concept are examined in detail, and the results for the two methods are compared.

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“…The approach given in equations 1 and 3 are the primary tools with which the impact of technology concepts will be evaluated in this paper ¶ . 19…”

Section: Second Law Methodsmentioning

confidence: 99%

Section: Case Study: High Speed Civil Transportmentioning

confidence: 99%

Analysis of advanced technology impact on HSCT engine cycle performance

Roth

Mavris

1999

35th Joint Propulsion Conference and Exhibit

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“…In the present case, the supersonic solution was used. For a more detailed discussion about stream-thrust analysis in general, refer to [26][27][28].…”

Section: Rear-side Truncationmentioning

confidence: 99%

Viscous Effects and Truncation Effects in Axisymmetric Busemann Scramjet Intakes

Flock

Gülhan

2016

AIAA Journal

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During Busemann intake design, two constraints have to be considered. First, caused by the displacement of the boundary layer, the pressure levels in a Busemann intake were higher (≈40%) than the values predicted analytically; these effects were labeled viscous effects. Second, truncating the flowfield also changed the properties of the classical Busemann flow; these effects were labeled truncation effects, and it can be distinguished between truncating the intake at the leading edge and at the rear side. To take into account viscous effects, the boundary-layer displacement thickness was calculated with an integral method and added to the inviscid Busemann contour. To quantify leadingedge truncation effects, an oblique shock at the leading edge was assumed, and the pressure at the intake exit was corrected with the continuity equation. The change in flow properties during the rear-side truncation was calculated with a stream-thrust analysis. The effects were separately investigated with Reynolds-averaged Navier-Stokes and Euler simulations, respectively. After the viscous correction, the deviation between numerically and analytically calculated pressure level was below 10%. When truncating the intake, the numerically calculated average pressure and temperature levels were within 1% of the analytical values.

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“…Lewis [10] provided clarification regarding the role of the second law in providing a universal definition of the propulsive efficiency for an isolated engine. The concept of thrust or thrust-work potential (also called stream-thrust based methods) for the performance characterization of high-speed ramjet and scramjet engines were first articulated by Curran and Craig [11]; considerable extension of their seminal work has been performed by Riggins et al [12,13]. The use of these methods has enabled the complete characterization of the loss in scramjet engine thrust due to irreversibility and has allowed the assessment of engine thrust losses in terms of irreversible loss mechanism and location.…”

mentioning

confidence: 99%

Characterization of Aerospace Vehicle Performance and Mission Analysis Using Thermodynamic Availability

Riggins

Moorhouse

Camberos

2010

Journal of Aircraft

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The fundamental relationship between entropy and aerospace vehicle and mission performance is analyzed in terms of the general availability rate balance between force-based vehicle performance, available energy associated with expended propellant, and the overall loss rate of availability, including the vehicle wake. The availability relationship for a vehicle is analytically combined with the vehicle equations of motion; this combination yields the balance between on-board energy rate usage and rates of changes in kinetic and potential energies of the vehicle and overall rate of entropy production. This result is then integrated over time for a general aerospace mission; as examples, simplified single-stage-to-orbit rocket-powered and air-breathing missions are analyzed. Examination of rate of availability loss for the general case of an accelerating, climbing aerospace vehicle provides a powerful loss superposition principle in terms of the separate evaluation and combination of loss rates for the same vehicle in cruise, acceleration, and climb. Rate of availability losses is also examined in terms of separable losses associated with the propulsion system and external aerodynamics. These loss terms are cast in terms of conventional parameters such as drag coefficient and engine specific impulse. Finally, rate losses in availability for classes of vehicles are described.

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The Use of Stream Thrust Concepts for the Approximate Evaluation of Hypersonic Ramjet Engine Performance

Cited by 31 publications

References 0 publications

Analysis of advanced technology impact on HSCT engine cycle performance

Analysis of advanced technology impact on HSCT engine cycle performance

Viscous Effects and Truncation Effects in Axisymmetric Busemann Scramjet Intakes

Characterization of Aerospace Vehicle Performance and Mission Analysis Using Thermodynamic Availability

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