scholarly journals Shock Waves Analysis of the Novel Intake Design Sytem for a Scramjet Propulsion

2021 ◽  
Vol 20 ◽  
pp. 67-75
Author(s):  
Abdulla Khamis Alhassani ◽  
Mohanad Tarek Mohamed ◽  
Mohammed Fares ◽  
Sharul Sham Dol
Keyword(s):  
Shock Waves ◽  
Gas Turbine ◽  
Aerospace Industry ◽  
Supersonic Combustion ◽  
The Novel ◽  
Turbine Engine ◽  
Pressure Losses ◽  
Air Stream ◽  
Compression Mechanism ◽  
Novel Design

The supersonic combustion scramjet in the inlet applies the shock waves compression mechanism tosubstitute the actual compressor from a gas turbine engine. The scramjet works with combustion of fuel throughthe air stream in supersonic condition at least with Mach 5. Novel design of a scramjet intake system was madewith variations in the angle of the fins and entrance width. The best combination of diameter and inclinationangle was 1.75 m and 15 degrees, respectively. The findings were able to increase the oblique shock waveinteractions and supplicate effective combustion and reduce pressure losses for the effective application ofscramjet system, which can be significant for aerospace industry.

Effect of Divergence Angle on Flow Through Inlet Section of Diffuser of a Gas Turbine Combustion Chamber: The CFD Approach

2006 ◽  
Author(s):  
Digvijay B. Kulshreshtha ◽  
S. A. Channiwala ◽  
Jitendra Chaudhary ◽  
Zoeb Lakdawala ◽  
Hitesh Solanki ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Total Pressure ◽  
Divergence Angle ◽  
Velocity Head ◽  
Turbine Engine ◽  
Inlet Velocity ◽  
Pressure Losses ◽  
Flow Through ◽  
Mach Numbers

In the combustor inlet diffuser section of gas turbine engine, high-velocity air from compressor flows into the diffuser, where a considerable portion of the inlet velocity head PT3 − PS3 is converted to static pressure (PS) before the airflow enters the combustor. Modern high through-flow turbine engine compressors are highly loaded and usually have high inlet Mach numbers. With high compressor exit Mach numbers, the velocity head at the compressor exit station may be as high as 10% of the total pressure. The function of the diffuser is to recover a large proportion of this energy. Otherwise, the resulting higher total pressure loss would result in a significantly higher level of engine specific fuel consumption. The diffuser performance must also be sensitive to inlet velocity profiles and geometrical variations of the combustor relative to the location of the pre-diffuser exit flow path. Low diffuser pressure losses with high Mach numbers are more rapidly achieved with increasing length. However, diffuser length must be short to minimize engine length and weight. A good diffuser design should have a well considered balance between the confliction requirements for low pressure losses and short engine lengths. The present paper describes the effect of divergence angle on diffuser performance for gas turbine combustion chamber using Computational Fluid Dynamic Approach. The flow through the diffuser is numerically solved for divergence angles ranging from 5 to 25°. The flow separation and formation of wake regions are studied.

Analysis of Indirectly Fired Gas Turbine for Wet Biomass Fuels Based on Commercial Micro Gas Turbine Data

2002 ◽  
Author(s):  
Brian Elmegaard ◽  
Bjo̸rn Qvale
Keyword(s):  
Gas Turbine ◽  
Process Integration ◽  
The Novel ◽  
Environmental Friendliness ◽  
Waste Products ◽  
Pressure Losses ◽  
Micro Gas Turbine ◽  
Typical Data ◽  
Wet Biomass ◽  
Simple Change

The results of a study of a novel gas turbine configuration is being presented. In this power plant, an Indirectly Fired Gas Turbine (IFGT), is being fueled with very wet biomass. The exhaust gas is being used to dry the biomass, but instead of striving to recover as much as possible of the thermal energy, which has been the practice up to now, the low temperature exhaust gases after having served as drying agent, are lead out into the environment; a simple change of process integration that has a profound effect on the performance. Four different cycles have been studied. These are the Simple IFGT fueled by dry biomass assuming negligible pressure loss in the heat exchanger and the combustion chamber, the IFGT fueled with wet biomass (Wet IFGT) assuming no pressure losses, and finally both the Simple and the Wet IFGT incorporating typical data for pressure losses of commercially available micro turbines. The study shows that the novel configuration, in which an IFGT and a drying unit have been combined, has considerable merit, in that its performance exceeds that of the currently available methods converting wet biomass to electric power by a factor of five. The configuration also has clear advantages with respect to corrosion and to the environmental friendliness and the quantity of the waste products and their usefulness.

scholarly journals Development of a Regenerator for an Automotive Gas Turbine Engine

1992 ◽  
Author(s):  
Junichi Sayama ◽  
Teru Morishita
Keyword(s):  
Velocity Distribution ◽  
Gas Turbine ◽  
Pressure Loss ◽  
Prediction Method ◽  
Gas Turbine Engine ◽  
Core Size ◽  
Turbine Engine ◽  
Pressure Losses ◽  
The Core ◽  
Core Matrix

It is vital to accurately estimate the temperature effectiveness and pressure loss of the regenerator when designing a gas turbine engine because these characteristics basically determine the size, weight, and fuel consumption of the regenerative gas turbine engine. In operation of an actual engine, regenerators often fail to attain the characteristics predicted by conventional methods, because there are many performance-reducing irregularities such as the non-uniform velocity distribution of gases flowing into the core. In this paper, a prediction method that is based on data from actual engine tests is examined as a way to predict regenerator temperature effectiveness and pressure losses when there are causes for deterioration of these characteristics. This method resulted in a system, taking the deterioration of these characteristics into consideration as they occur in an actual engine, that represents temperature effectiveness and pressure loss as the function of core specifications such as the core size and the core matrix. This prediction method was then used to predict the regenerator characteristics of actual engines with more than satisfactory results (The accuracy is ±1.25% for temperature effectiveness and ±4% for pressure loss).

A New 1.7MW Industrial Gas Turbine: The Ruston Hurricane

1991 ◽  
Author(s):  
A. T. Sanders ◽  
M. H. Tothill ◽  
G. R. Wood
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Thermodynamic Efficiency ◽  
The Novel ◽  
Exhaust Temperature ◽  
High Pressure Ratio ◽  
Industrial Gas Turbine ◽  
Novel Design

The paper describes the design of a compact new 1.7MW (2300hp) single shaft industrial gas turbine and package, with high efficiency and exhaust temperature ideal for industrial congeneration applications. These advantages are obtained with a high pressure ratio single stage centrifugal compressor, single high temperature combustor and two-stage axial flow turbine using only one row of cooled blades. The novel design features are described with the associated development testing. A typical installation is also described showing the potential for very high overall thermodynamic efficiency.

Development of a Regenerator for an Automotive Gas Turbine Engine

1993 ◽  
Vol 115 (2) ◽  
pp. 424-431 ◽  
Author(s):  
J. Sayama ◽  
T. Morishita
Keyword(s):  
Velocity Distribution ◽  
Gas Turbine ◽  
Pressure Loss ◽  
Prediction Method ◽  
Gas Turbine Engine ◽  
Core Size ◽  
Turbine Engine ◽  
Pressure Losses ◽  
The Core ◽  
Core Matrix

It is vital to estimate the temperature effectiveness and pressure loss of the regenerator accurately when designing a gas turbine engine because these characteristics basically determine the size, weight, and fuel consumption of the regenerative gas turbine engine. In operation of an actual engine, regenerators often fail to attain the characteristics predicted by conventional methods, because there are many performance-reducing irregularities such as the nonuniform velocity distribution of gases flowing into the core. In this paper, a prediction method that is based on data from actual engine tests is examined as a way to predict regenerator temperature effectiveness and pressure losses when there are causes for deterioration of these characteristics. This method resulted in a system, taking the deterioration of these characteristics into consideration as they occur in an actual engine, that represents temperature effectiveness and pressure loss as the function of core specifications such as the core size and the core matrix. This prediction method was then used to predict the regenerator characteristics of actual engines with more than satisfactory results (the accuracy is ±1.25 percent for temperature effectiveness and ±4 percent for pressure loss).

A Novel Approach to the Stabilization of Auto-Igniting Flames Within a Gas Turbine Sequential Combustor, Through the Control of Static Temperature Variation Along the Premixing and Flame Zones

2020 ◽  
Author(s):  
K. J. Syed ◽  
A. C. Benim ◽  
E. Pasqualotto ◽  
R. C. Payne
Keyword(s):  
Gas Turbine ◽  
Pressure Loss ◽  
The Novel ◽  
Turbine Stage ◽  
Critical Aspect ◽  
Single Digit ◽  
Pressure Losses ◽  
Hot Gas ◽  
Novel Approach ◽  
Novel Concept

Abstract The present work proposes a novel concept for a sequential burner and combustor that can be located downstream of a first stage combustor or downstream of a turbine stage in the case of a reheat gas turbine. The novel aspect is the method of flame anchoring, which, instead of relying on dump expansion as in the present state-of-the-art, relies on setting up a static temperature gradient through the premixing and flame zones. The advantage of this is that anchoring of the auto-igniting flame is not dependent on fluid mechanic phenomena, and reaction can proceed at rates governed by the chemical kinetics. Under these circumstances, CO can reach its equilibrium in ≪ 1ms, which allows for compactness and the potential of single digit NOx emissions at hot gas temperatures in excess of 2100K. Pressure loss is a critical aspect, as the concept requires flows to be accelerated to high velocities (M∼0.7). However, it is shown that pressure losses can be limited to 4–5%. The concept is evaluated through analytical and 1D approaches, while the feasibility of achieving a design that meets the desired turbulence characteristics at an acceptable pressure loss is demonstrated by way of 3D CFD.

Perfect Heat Recovery From a Partial Oxidation Gas Turbine Engine

1999 ◽  
Author(s):  
Frederick W. Call
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Synthesis Gas ◽  
Perfect Match ◽  
Complete Recovery ◽  
Turbine Engine ◽  
Gas Streams ◽  
Air Stream ◽  
Exhaust Heat ◽  
Gas Turbine Power Plant

Abstract This paper shows how to obtain the complete recovery of exhaust heat in the context of a gas turbine power plant. The power plant uses partial combustion of the fuel and yields power and a synthesis gas for further use in a chemical plant or conventional steam power plant. The key is a heat exchanger in conjunction with a Ni/NiO chemical loop that alters the composition of the air stream so that there is nearly a perfect match of the hot and cold streams down to ambient temperature. The chem-loop removes the oxygen for fuel combustion from the air as it raises the temperature of both the water/air and the synthesis gas streams (only the latter is used for power production). Assuming no heat losses from unit operations, no parasitic losses, and a pinch of only 2°C (simultaneous boiling and condensing) the First Law efficiency of the power plant can be over 98% (Second Law is about 45%). There are no acidic stack gases to contend with at this point as the partially combusted fuel is then exported for other uses, its value diminished only by the amount of power produced.

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