Experimental Research of Fuel Mass Flow Rate Distribution Effectiveness in Fuel Manifold on Engine Starting Performance

Measurements are presented for the flow in the tip gap of a planar cascade of turbine blades. Three clearances of from 2.0 to 3.2 percent of the blade chord were considered. Detailed surveys of the velocity magnitude, flow direction, and total pressure within the gap were supplemented by blade surface and endwall static pressure measurements. The results help to clarify the relationship between the leakage mass flow rate distribution and the driving pressure differences. It was found that even for the present relatively large clearances, fluid near the endwall experiences a pressure difference that is comparable with the blade pressure difference. It is also shown that a simple model can predict with good accuracy the mass flow rate distribution and the magnitude and direction of the velocity vectors within the gap.

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Effects of Burner Diameter and Fuel Type on Smoke Point and Radiation Characteristics of Diffusion Flames

Engineering Technology Conference on Energy, Parts A and B ◽

10.1115/etce2002/cae-29011 ◽

2002 ◽

Author(s):

S. F. Goh ◽

S. Kusadomi ◽

S. R. Gollahalli

Keyword(s):

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

Critical Mass ◽

Smoke Point ◽

Fuel Type ◽

Fuel Flow Rate ◽

Flame Radiation ◽

Fuel Mass ◽

Fuel Flow

The main purpose of this study was to comprehend the effects of burner diameter and fuel type on smoke point characteristics of a hydrocarbon diffusion flame and its radiation emission. The critical mass flow rate of pure fuel at this smoke point was measured. At nine different fractions of the critical mass flow rate, nitrogen gas was supplied along with the fuel to achieve smoke point. At each condition, flame radiation and flame height were measured. The axial radiation profile at the critical fuel mass flow rate for one burner was also measured. Three fuels of differing sooting propensities were used: ethylene (C2H4), propylene (C3H6), and propane (C3H8). Three different burners with inner diameters of 1.2 mm, 3.2 mm and 6.4 mm were used. Results showed that propylene had the highest critical fuel flow rate and the highest nitrogen dilution required to suppress smoking and total flame radiation, followed by ethylene and propane. For all fuels, the curves of nitrogen flow rate required for smoke suppression versus fuel flow rate exhibited a skewed bell shape. The variation of Reynolds number at the critical fuel mass flow rate with the burner diameter showed a linear relation. On the other hand, the variation of total flame radiation with burner diameter was nonlinear.

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Investigating the effect of duct burner fuel mass flow rate on exergy destruction of a real combined cycle power plant components based on advanced exergy analysis

Energy Conversion and Management ◽

10.1016/j.enconman.2015.07.008 ◽

2015 ◽

Vol 103 ◽

pp. 827-835 ◽

Cited By ~ 17

Author(s):

Fateme Ahmadi Boyaghchi ◽

Hanieh Molaie

Keyword(s):

Power Plant ◽

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

Exergy Analysis ◽

Combined Cycle ◽

Exergy Destruction ◽

Fuel Mass ◽

Duct Burner ◽

Plant Components

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EFFECTS OF THE VARIATION OF INJECTION PRESSURE AND ENERGIZING TIME ON INJECTORS FUEL MASS FLOW RATE

10.26678/abcm.cobem2019.cob2019-0805 ◽

2019 ◽

Author(s):

Bruno Ferreira ◽

Daniel Sales Santos Machado ◽

Alex de Oliveira ◽

Marco Aurélio Justino ◽

Vinicius Guerra Moreira ◽

...

Keyword(s):

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

Injection Pressure ◽

Fuel Mass

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The response of the solid fuel ramjet combustor to the inflow excitations

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/09544100211053405 ◽

2021 ◽

pp. 095441002110534

Author(s):

AmirMahdi Tahsini ◽

Seyed Saeid Nabavi

Keyword(s):

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

Solid Fuel ◽

Ambient Pressure ◽

Excitation Frequency ◽

Engine Performance ◽

Computational Domain ◽

Rocket Motors ◽

Fuel Mass

The response of the solid fuel ramjet to the imposed excitations of the ambient pressure is investigated using full part computation of the system including the intake, combustion chamber, and exhaust nozzle. The finite volume solver of the turbulent reacting compressible flow is used to simulate the flow field, where two grid blocks are considered for discretizing the computational domain. Both impulsive and oscillatory excitations are imposed to predict the response of the solid fuel mass flow rate. The results demonstrate that strong fuel flow overshoot occurs in the case of sudden impulsive excitation which is omitted for gradual impulsive excitations. In addition, the oscillatory excitations eventually lead to regular oscillatory response with frequencies similar to the imposed excitations and decrease the average fuel mass flow rate independent of the excitation frequency. But the amplitude of the response depends on the excitation frequency and amplification occurs in some frequencies. This behavior is not related to the combustion instabilities and is similar to the L-star instability in the solid rocket motors. In the design and analysis of the solid fuel ramjets, the coupling of the flight dynamics and the engine performance must be considered, and this study is the first step of such complete methodology to have more accurate predictions.

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