Pulse Combustor Driven Pressure Gain Combustion for High Efficiency Gas Turbine Engines

Lisanti, Joel C.; Roberts, William L.

doi:10.1007/978-981-10-3785-6_7

Cited by 11 publications

(9 citation statements)

References 27 publications

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“…Despite the important research effort that the detonation combustion based pressure gain combustion have drawn [3][4][5], the inefficiency caused by poor coupling between the detonation portion of the engine and the turbo machinery still possess a significant challenge. The high velocity of the detonation front (order of km/s) and the intrinsic high unsteadiness property makes it extraordinarily difficult to implement into a gas turbine system [6]. Because of this, the deflagration based pulse combustion engine has gained significant attention from both industry and academia due to the considerable potential of high efficiency, low pollutant emission [1,7], and flexibility of implementation in real engine systems.…”

Section: Introductionmentioning

confidence: 99%

“…Based on the inlet valve geometry, pulse combustors are usually classified into two categories, namely valveless [10,11] and valved [12,13]. Recently, Lisanti and Roberts [6,14,15] developed a novel actively valved pulse combustor with rotary valve for pressure gain combustion applications. The low mass passive valve was replaced with a ball shaped rotary valve allowing for much more durable operation.…”

Section: Introductionmentioning

confidence: 99%

“…With the results, a general concept of the operational properties of the actively valved pulse combustor with gaseous fuel were understood. In the previous work [6,14,15] all of the data collection was focused on a single axial location so that the variation along the axial location and the global sense of the combustion/acoustic coupling have not been elucidated. However, the combustion information in the downstream of the combustor shows an identical influence in governing the operational performance of the combustor.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A Preliminary Investigation of the Secondary Flame and Operational Properties of an Actively-valved Pulse Jet

Zhu

Lisanti

Guiberti

et al. 2020

AIAA Scitech 2020 Forum

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Due to their complex nature, a clear and comprehensive understanding of the mechanisms driving the combustion dynamics of pulse jets is not yet available. The present work intends to fill this gap by shedding some light on general operational properties of an active valve resonant pulse combustor as well as fundamental mechanisms. Pressure sensors and ion probes were used to quantify the global performance of the pulse combustor in naturallyaspirated mode or for different forced air flow-rates. It was shown that performance, here indicated by the pressure gain, improves when the forced air flow-rate increases. For a subset of operating conditions, infrared and thermocouple thermometry was used to measure side wall temperatures. Gas sampling was also used to infer species concentrations inside the combustor and along its main axis. These measurements highlighted the presence of a secondary flame located in the tail pipe, near the exhaust. A possible mechanism responsible for this secondary flame was proposed.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

A Preliminary Investigation of the Secondary Flame and Operational Properties of an Actively-valved Pulse Jet

Zhu

Lisanti

Guiberti

et al. 2020

AIAA Scitech 2020 Forum

Self Cite

View full text Add to dashboard Cite

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“…In their study the PDC was directly attached to the turbine without any additional devices in between. If the PDC is not carefully integrated with the turbine components, these phenomena could easily eliminate any potential gain in cycle efficiency provided from PGC [7]. One possible approach for coupling of PDCs and a downstream turbine would be using shape optimized devices.…”

Section: Introductionmentioning

confidence: 99%

Investigation of the Exhaust Flow of a Pulse Detonation Combustor at different Operating Conditions based on High-Speed Schlieren and PIV

Haghdoost

Edgington-Mitchell²,

Paschereit

et al. 2019

AIAA Scitech 2019 Forum

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The exhaust flow of a Pulse Detonation Combustor (PDC) is investigated for different operating conditions. The PDC consists of two units, the deflagration to detonation transition section and the exhaust tube with a straight nozzle. High-speed high-resolution schlieren images visualize the shock dynamics downstream of the nozzle. The flow dynamics during one full PDC cycle is examined via high-speed Particle Image Velocimetry. A well-suited solid tracer particle for supersonic reactive flow is determined in a preliminary study to minimize the PIV measurement error. The investigated operating conditions of the PDC differ in fillfraction, which is the percentage of the tube filled with a reactive mixture. With increasing fill-fraction, the flow features grow in size and strength, as the propagation velocity of the leading shock increases. The blow down process of the PDC is characterized by several exhaust and suction phases. An increase in fill-fraction results in a stronger first exhaust phase, while the subsequent suction and exhaust phases remain almost unaffected.

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“…D to the inherent efficiency gains associated with pressure-gain combustion, much research effort has been dedicated to this field in recent years [1][2][3]. Although much attention is currently being given to the rotating detonation engine, other concepts, such as the pulse jet and the pulse detonation engine continue to be viable concepts for advanced pressure-gain cycles.…”

Section: Introductionmentioning

confidence: 99%

Effects of Nanosecond Repetitively Pulsed Plasma Discharges on a Propagating Hydrogen--Air Flame

Gray

Lacoste

2019

AIAA Scitech 2019 Forum

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Pressure-gain combustion cycles have been a topic of intense scientific research in recent years. Pulse detonation combustors are one promising technology for successfully implementing these pressure-gain cycles. These combustors frequently rely on obstacles for accelerating a propagating flame and inducing the deflagration-to-detonation transition. The use of obstacles, however, has several disadvantages. Replacing such obstacles with nanosecond repetitively pulsed plasma discharges may be advantageous to developing this technology further. Proof of concept has been achieved demonstrating the effectiveness of this strategy at enhancing the transition to detonation. This work is a closer investigation into the effect of these plasma discharges on flames with varying turbulence intensities and propagation velocities. For velocities below 200 m/s, the effect is minimal and transition to detonation does not occur. The effect of plasma discharges on flame acceleration also begins to diminish for the current configuration and pulse repetition frequency at speeds above 400 m/s. This give a range where nanosecond repetitively pulsed plasma discharges may be used effectively for efficient flame acceleration and transition to detonation.

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Pulse Combustor Driven Pressure Gain Combustion for High Efficiency Gas Turbine Engines

Cited by 11 publications

References 27 publications

A Preliminary Investigation of the Secondary Flame and Operational Properties of an Actively-valved Pulse Jet

A Preliminary Investigation of the Secondary Flame and Operational Properties of an Actively-valved Pulse Jet

Investigation of the Exhaust Flow of a Pulse Detonation Combustor at different Operating Conditions based on High-Speed Schlieren and PIV

Effects of Nanosecond Repetitively Pulsed Plasma Discharges on a Propagating Hydrogen--Air Flame

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