Experimental Investigations of the Performance of a Multitube Pulse Detonation Turbine System

Rasheed, Adam; Furman, Anthony; Dean, Anthony J.

doi:10.2514/1.53830

Cited by 6 publications

(8 citation statements)

References 22 publications

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“…The experimental and computational findings on partial admission would indicate that performance would not suffer degradation, at least over a certain frequency range for certain favorable cycle characteristics. Comparable PDC-Turbine system findings are obscured by the existence of bypass flows 10,13,58 , which effectively create an additional volume with its own wave dynamics, filling-and-emptying behavior, and transmission of signals between adjacent turbine entry points. This frequency interaction could excite certain structural modes within the system, limiting the operating range 57 , or amplify existing aerodynamic modes within the turbine 2 .…”

Section: Figure 9 Variation Of Output Power and Rotor Speed In A Pdcmentioning

confidence: 93%

“…Replacing the conventional turbine models, which are currently limited to single values of isentropic efficiency, or a steady performance map, with a fully unsteady modeling of the passages, and potentially a frozen-rotor approach, could greatly increase the accuracy of these models in predicting the gross system performance. With ongoing current investigations 12,13 and upcoming future investigations at the University of Cincinnati, a wealth of experimental data might soon be available to validate such a tool. The integration of the sophisticated PDC model with an equally refined turbine model then will provide the designer with a vital tool for the development and optimization of the PDC-Turbine Hybrid System.…”

Section: Figure 9 Variation Of Output Power and Rotor Speed In A Pdcmentioning

confidence: 96%

“…[9][10][11][12][13] While conventional turbine engines employ the constant pressure Brayton-cycle combustion, an idealized thermodynamic analysis 14 indicates that a near constant volume combustion (CVC) cycle such as pulse detonation combustion (PDC) can provide a sizeable increase in thermal efficiency. This consideration, coupled with lower combustion temperatures for comparable combustor exit pressure has the potential to both reduce thermal loading on the turbine and downsize the required compressor.…”

Section: Introductionmentioning

confidence: 99%

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Trends in Pulsating Turbine Performance: Pulse-Detonation Driven Axial Flow Turbine

George

Gutmark

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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An investigation of previous studies involving turbines driven by pulsating, unsteady flows is conducted. The suitability of conventional steady flow performance metrics for application to the case of pulsating flow is discussed, with a focus on the observed deviation from quasi-steady behavior. This deviation is found to be a strong function of upstream geometry, pulse form and amplitude, and disparity between the time scales of the pulse and of the rotor dynamics. Existing studies exhibit controversy as to the effects of parametric variation of pulsating flow quantities on the turbine performance as well as suitable metrics to describe this performance. These studies are used to predict qualitative trends for the performance of an integrated pulse-detonation driven axial turbine. Trends from current experimental studies of pulse-detonation driven flows are examined to assess these hypotheses. Nomenclaturea = Sonic Velocity (m/s) PDC = Pulse Detonation Combustion AF = Amplitude Factor PDE = Pulse Detonation Engine BSR = Blade Speed Ratio, Velocity Ratio PMSt = Pressure Modified Strouhal Number C = Absolute Flow Velocity (m/s) PR = Pressure Ratio c p = Specific Heat at Constant Pressure (J/kg·K) QSF = Quasi-Steady Flow CVC = Constant Volume Combustion St = Strouhal Number d = Diameter (m) T = Temperature (K) f = Frequency of Pulsation (Hz) U = Rotor Tip (Blade) Speed (m/s) h = Specific Enthalpy (J/kg) v = Mean Flow Velocity (m/s) L = Characteristic Length (m) W = Relative Flow Velocity (m/s) ṁ = Mass Flow Rate (kg/s) x = Arbitrary Spatial Location MFP = Mass Flow Parameter (K ½ ·s/m) β = Reduced Frequency MSt = Modified Strouhal Number γ = Ratio of Specific Heats N = Turbine Speed (rad/s) η = Efficiency T N / = Normalized Turbine Speed (rad/K ½ s) φ = Duty Cycle P = Power (W), Pressure (Pa) τ = Torque (N·m) ω = Frequency of Pulsation (rad/s)

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Section: Figure 9 Variation Of Output Power and Rotor Speed In A Pdcmentioning

confidence: 93%

Section: Figure 9 Variation Of Output Power and Rotor Speed In A Pdcmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Trends in Pulsating Turbine Performance: Pulse-Detonation Driven Axial Flow Turbine

George

Gutmark

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

show abstract

“…Glaser et al [29,30] conducted experimental investigations into thrust performance of valved multitube PDE with different nozzle geometries and the pressure rise in the PDE was quantified. Rasheed et al [31][32][33][34] studied performance of a multi-tube pulse detonation combustor turbine system. This hybrid system consisted of eight tubes and operated with three firing patterns using ethylene-air mixtures.…”

Section: Introductionmentioning

confidence: 99%

Operating characteristics and propagation of back-pressure waves in a multi-tube two-phase valveless air-breathing pulse detonation combustor

Lü

Zheng

Wang

et al. 2015

Experimental Thermal and Fluid Science

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“…To harness these potential gains and dramatically boost system performance, existing turbomachinery must be appropriately matched and optimized for a periodic unsteady combustor flow. This presents a significant integration challenge, and many studies have aimed to characterize turbine performance driven by pulse detonation flows [2][3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Axial Turbine Performance Driven by Steady and Pulsating Flows

George

Driscoll

Stoddard

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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A series of experiments are conducted to characterize the effects of pulse frequency on the performance of an axial turbine under pulsating flow. A steady flow turbine map is generated over the range of interest for comparison to the pulsed flow results. An investigation of steady partial admission performance provides additional explanation for trends in the pulsating case. High frequency response probes are implemented to obtain time-resolved temperature, static pressure, and total pressure across the turbine stage. Various formulations of efficiency as well as other figures of merit are generated from these data to provide a direct comparison to the steady flow cases. Nomenclature hp = Horsepower PDE = Pulse Detonation Engine m & = Mass Flow Rate (kg/s) P s = Specific Power MFP = Mass Flow Parameter (kg·K 1/2 /Pa) psig = Pounds per square inch, gauge Ndes = Turbine Design Speed T 0 = Total Temperature PDC = Pulse Detonation Combustion τ = Torque (N·m)

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Experimental Investigations of the Performance of a Multitube Pulse Detonation Turbine System

Cited by 6 publications

References 22 publications

Trends in Pulsating Turbine Performance: Pulse-Detonation Driven Axial Flow Turbine

Trends in Pulsating Turbine Performance: Pulse-Detonation Driven Axial Flow Turbine

Operating characteristics and propagation of back-pressure waves in a multi-tube two-phase valveless air-breathing pulse detonation combustor

Experimental Investigation of Axial Turbine Performance Driven by Steady and Pulsating Flows

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