Effect of Periodic Pressure Pulses on Axial Turbine Performance

Fernelius, Mark; Gorrell, Steven E.; Hoke, John; Schauer, Frederick

doi:10.2514/6.2013-3687

Cited by 10 publications

(4 citation statements)

References 4 publications

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“…As a consequence, the instantaneous field is expressed as the summation of the mean value and the fluctuating component for both scalars (e.g., ϕ = ϕ + ϕ ′ ) and vectors (e.g., u i = u i + u ′ i ). Thus, by taking a time (or ensemble) average and dropping the overbar on the quantities except for products of fluctuating quantities, the URANS equations are reported in Equations ( 18)- (20).…”

Section: Governing Equationsmentioning

confidence: 99%

“…The latter case has gained great interest from researchers despite the fact that turbomachinery is fundamentally based on a steady design approach. Fernelius et al [20] demonstrated experimentally that the full-annulus pulsation of an axial turbine deteriorated its efficiency, while the variation of the incidence angle [21] was the major performance parameter. Moreover, they tried to map the turbine's efficiency under pulsation [22] in order to offer recommendations for the design of these pioneering turbine airfoils [23].…”

Section: Introductionmentioning

confidence: 99%

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Development of 1D Model of Constant-Volume Combustor and Numerical Analysis of the Exhaust Nozzle

Gallis,

Misul,

Boust

et al. 2024

Energies

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Pressure gain combustion cycles are under the spotlight due to their higher theoretical cycle thermal efficiency compared to conventional machines. Under this prism, a constant-volume combustor (CVC) prototype supplied with a mixture of air and liquid iso–octane was developed. The efforts of the current study were focused on both creating a 1D model of the experimental test rig for the CVC analysis and a 3D numerical simulation of the exhaust system. The goal of the study was to retrieve the total outlet quantities of the combustor, which would otherwise be difficult to assess experimentally, and to investigate the pulsating flow field at the outlet. First, a thorough description of the reduced order model was accompanied with the model’s validation using the available experimental data of the chamber. Then, the resulting outlet stagnation properties of the CVC were imposed as spatially averaged transient boundary conditions to the 3D exhaust flow domain. The unsteady Reynolds–averaged Navier–Stokes equations were solved for a sufficient number of periods, and the assessment of the out-take system in terms of losses and attenuation was conducted. In conclusion, the analysis of the combustor’s outflow will pave the way for an effective future design of the CVC exhaust system.

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Section: Governing Equationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Development of 1D Model of Constant-Volume Combustor and Numerical Analysis of the Exhaust Nozzle

Gallis,

Misul,

Boust

et al. 2024

Energies

View full text Add to dashboard Cite

show abstract

“…The relevant studies show that, the unsteady exhaust of the PDC could lead to local separation bubbles on the turbine blades, and further increase the boundary layer loss of the turbine [54]; the effects of unsteady flow from the PDC on the axial turbine efficiency is not significant if the PDC exhaust is mixed with the steady bypass flow [55]. The performance analysis of the axial flow turbine under high-amplitude, high-frequency pulsating flow conditions shows that the turbine efficiency is closely related to the corrected mass flow and mass flow averaged rotor blade intake angle [56][57].…”

Section: System Configuration and Component Matchingmentioning

confidence: 99%

Review on the Rotating Detonation Engine and It’s Typical Problems

Xie

Wen

et al. 2020

Transactions on Aerospace Research

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Detonation is a promising combustion mode to improve engine performance, increase combustion efficiency, reduce emissions, and enhance thermal cycle efficiency. Over the last decade, significant progress has been made towards the applications of detonation mode in engines, such as standing detonation engine (SDE), Pulse detonation engine (PDE) and rotating detonation engine (RDE), and the understanding of the fundamental chemistry and physics processes in detonation engines via experimental and numerical studies. This article is to provide a comprehensive overview of the progress in the knowledge of rotating detonation engine from the different countries. New observations of injection, ignition, and geometry of combustor, pressure feedback, and combustion modes of RDE have been reported. These findings and advances have provided new opportunities in the development of rotating detonation for practical applications. Finally, we point out the current gaps in knowledge to indicate which areas future research should be directed at.

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“…Rather the crucial question is whether the pressure gains that have been achieved will not be lost (and more) when the unsteady PGC combustor is integrated into the engine turbomachinery. Some work on this has been undertaken principally for the turbine (see Fernelius et al (61) ), but no work has yet been reported on compatibility with the compressor. Ward and Miller (62) have demonstrated that the addition of an unsteady ejector at the exit of the Cambridge/Rolls Royce PGC device (to reduce unsteadiness and allow adjustment/ integration with the downstream NGV flow) allows retention of ~70% of the pressure gain, but this has so far only been demonstrated for a simple laboratory system.…”

Section: Pressure Gain Combustionmentioning

confidence: 99%

The aerodynamic challenges of aeroengine gas-turbine combustion systems

McGuirk

2014

Aeronaut. j. (1968)

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The components of an aeroengine gas-turbine combustor have to perform multiple tasks -control of external and internal air distribution, fuel injector feed, fuel/air atomisation, evaporation, and mixing, flame stabilisation, wall cooling, etc. The 'rich-burn' concept has achieved great success in optimising combustion efficiency, combustor life, and operational stability over the whole engine cycle. This paper first illustrates the crucial role of aerodynamic processes in achieving these performance goals. Next, the extra aerodynamic challenges of the 'lean-burn' injectors required to meet the ever more stringent NO x emissions regulations are introduced, demonstrating that a new multi-disciplinary and 'whole system' approach is required. For example, high swirl causes complex unsteady injector aerodynamics; the threat of thermo-acoustic instabilities means both aerodynamic and aeroacoustic characteristics of injectors and other air admission features must be considered; and high injector mass flow means potentially strong compressor/combustor and combustor/turbine coupling. The paper illustrates how research at Loughborough University, based on complementary use of advanced experimental and computational methods, and applied to both isolated sub-components and fully annular combustion systems, has improved understanding and identified novel ideas for combustion system design.

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Effect of Periodic Pressure Pulses on Axial Turbine Performance

Cited by 10 publications

References 4 publications

Development of 1D Model of Constant-Volume Combustor and Numerical Analysis of the Exhaust Nozzle

Development of 1D Model of Constant-Volume Combustor and Numerical Analysis of the Exhaust Nozzle

Review on the Rotating Detonation Engine and It’s Typical Problems

The aerodynamic challenges of aeroengine gas-turbine combustion systems

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