Application of Inlet Injection to a Three-Dimensional Scramjet at Mach 8

Turner, James C.; Smart, Michael K.

doi:10.2514/1.j050052

Cited by 58 publications

(27 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…This methodology has the advantage of significantly increasing mixing length without increasing the overall length of the engine. The fuel can be mixed significantly prior to the combustor entrance allowing for the combustor length to be shortened and the overall performance of the vehicle to be improved (Turner and Smart, 2010).…”

Section: Inlet Injectionmentioning

confidence: 99%

“…Despite these potential drawbacks, inlet injection can potentially improve the performance of hypervelocity scramjet engines where mixing length dominates combustion chamber length which is pertinent to overall performance (Turner and Smart, 2010).…”

Section: Inlet Injectionmentioning

confidence: 99%

“…A recent investigation by Turner and Smart (2010) which applied inlet injection to a three dimensional hydrogen fuelled scramjet engine at a Mach 8.1 flight condition showed it to be a viable alternative. The experiments showed that inlet injection did not disrupt the operation of the three dimensional inlet and robust combustion of the hydrogen fuel was observed at equivalence ratios approaching 1.…”

Section: Inlet Injectionmentioning

confidence: 99%

See 2 more Smart Citations

Experimental investigation of a three dimensional scramjet engine at hypervelocity conditions

Wise¹

View full text Add to dashboard Cite

Air-breathing propulsion has the ability to provide more economical access-to-space than current rocket based systems. Access-to-space requires hypersonic flight within the atmosphere, the air-breathing cycle best suited to this is the scramjet. Next generation launch systems require a scramjet stage to operate into the hypervelocity regime (> 3 km/s). Performance data at these conditions is scarce due to the inability of ground test facilities to replicate the high total pressures and temperatures associated with flight. Also, flight experiments are subject to material limitations and are generally prohibitively expensive. This thesis details experiments which add to the currently limited data-set of scramjet performance at hypervelocity conditions.The Mach 12 rectangular-to-elliptical shape-transitioning (RESTM12) engine is currently under investigation at The University of Queensland as a potential candidate for access-to-space. The RESTM12 engine is designed to accelerate from Mach 6-12 as a part of a rocket-scramjet-rocket access-to-space system. Previous testing of the RESTM12 engine has shown good performance at off-design conditions and now as a result of this investigation, robust performance at its design condition.The primary aim of this thesis was to:"investigate experimentally whether robust supersonic combustion can be generated in a three-dimensional scramjet flowpath at a Mach 12 flight condition in an impulse facility."In order to achieve this two experimental campaigns where undertaken in the T4 Stalker Tube. Both experiments used the facilities Mach 10 nozzle to generate a test flow equivalent to Mach 11.8 flight at 38.3 km altitude. Initial experiments investigating hypervelocity boundary layer transition showed that natural transition would not occur in a length equivalent to the forebody and inlet of the engine. The ingestion of a laminar boundary layer into the inlet of the RESTM12 engine would increase the likelihood of developing a separation in the inlet that would not allow it to operate as intended. To reduce the susceptibility of the inlet to separation a boundary layer trip was required.i Based on the Hyper-X program's boundary layer trip development experiments (Berry et al., 2001a), several combinations of trip geometry, height and location were tested on a flat plate model resulting in a successful trip configuration. Now confident that a trip configuration capable of providing the RESTM12 engine with a turbulent boundary layer was designed, the engine was tested at its design condition.A half-scale model of the RESTM12 scramjet engine was tested in a semi-free-jet configuration utilising both inlet and step injection of gaseous hydrogen fuel. Once it was established that the inlet was operating correctly and sufficient test time was available the experiments began with fuel injection. Initial tests showed that robust combustion occurred when inlet injection was employed. The most successful fuelling configuration was a combined injection scheme where 31% of the fuel was ...

show abstract

Section: Inlet Injectionmentioning

confidence: 99%

Section: Inlet Injectionmentioning

confidence: 99%

Section: Inlet Injectionmentioning

confidence: 99%

See 1 more Smart Citation

Experimental investigation of a three dimensional scramjet engine at hypervelocity conditions

Wise¹

View full text Add to dashboard Cite

show abstract

“…Исторический обзор выполнен-ных обширных исследований интенсификации смешения применительно к ГПВРД с помощью различных механических устройств дан в рабо-те [1]. Возможности улучшения смешения и эффективности горения путем предварительной подачи струи топлива в набегающий поток перед воздухозаборником или в изоляторе перед камерой сгорания анализировались в работах [2,3]. В качестве перспективного способа воздействия на эти процессы в настоящее время рассматривается подвод энергии с помощью оптических и электрических разрядов [4][5][6].…”

Section: поступило в редакцию 31 января 2017 гunclassified

Влияние Локализованного Импульсно-Периодического Подвода Энергии На Сверхзвуковое Смешение В Каналах

Желтоводов¹,

Пимонов²

2017

Письма В Журнал Технической Физики

View full text Add to dashboard Cite

На основе численного моделирования сверхзвуковых течений в плоских каналах с сужающимися и расширяющимися входными участками обосновывается возможность интенсификации смешения сверхзвуковой газовой струи пониженной плотности с окружающим спутным сверхзвуковым потоком с помощью локализованного импульсно-периодического подвода энергии. Демонстрируется влияние положения струи и энергоисточника на формирование крупномасштабных вихревых структур, сопутствующих интенсификации процесса смешения. DOI: 10.21883/PJTF.2017.16.44929.16723

show abstract

“…Such a design could be used to increase the performance at high Mach numbers without the need for variable geometry. Inlet injection has shown promise in high-Mach-number scramjets such as the radical farming scramjets [17][18][19] and the rectangular-to-elliptical shape transition (REST) engine [20]. Radical farming scramjets typically employ nominally two-dimensional (2-D) and axisymmetric inlet compression geometries, whereas the REST engine has an inlet designed from stream tracing within an axisymmetric flowfield.…”

mentioning

confidence: 99%

Numerical Investigation into the Combustion Behavior of an Inlet-Fueled Thermal-Compression-Like Scramjet

2015

View full text Add to dashboard Cite

A numerical study on the combustion behavior of an inlet-fueled three-dimensional nonuniform-compression scramjet is presented. This paper is an extension to previous work on the combustion processes in a premixed threedimensional nonuniform-compression scramjet, where thermal compression was shown to enhance combustion. This paper demonstrates how thermal compression can be used in a generic scramjet configuration with a realistic fuelinjection method to enhance performance at high flight Mach numbers. Such a scramjet offers an extra degree of freedom in the design process of fixed-geometry scramjets that must operate over a range of flight Mach numbers. In this study, how the combustion processes are affected is investigated, with the added realism of inlet porthole fuel injection. Ignition is established from within a shock-induced boundary-layer separation at the entrance to the combustor. Radicals that form upstream of the combustor within the inlet, from the injection method, enhance combustion. Coupling of the inlet-induced spanwise gradients and thermal compression improves combustion. The results highlight that, although the fuel-injection method imparts local changes to the flow structures, the global flow behavior does not change compared to previous premixed results. This combustion behavior will be reproduced when using other fueling methods that deliver partially premixed fuel and air to the combustor entrance.

show abstract

Application of Inlet Injection to a Three-Dimensional Scramjet at Mach 8

Cited by 58 publications

References 28 publications

Experimental investigation of a three dimensional scramjet engine at hypervelocity conditions

Experimental investigation of a three dimensional scramjet engine at hypervelocity conditions

Влияние Локализованного Импульсно-Периодического Подвода Энергии На Сверхзвуковое Смешение В Каналах

Numerical Investigation into the Combustion Behavior of an Inlet-Fueled Thermal-Compression-Like Scramjet

Contact Info

Product

Resources

About