A New Design of a Pinwheel-Shaped High-g Combustor

2021 ◽  
Author(s):  
Yu Liu ◽  
Zishuo Wang ◽  
Hao Tang
Keyword(s):  
Weight Ratio ◽  
Flow Distribution ◽  
Gas Turbine Combustor ◽  
Inlet Channel ◽  
Turbine Engine ◽  
Engine Efficiency ◽  
Design Iteration ◽  
Engine Thrust ◽  
Final Design ◽  
Exit Temperature

Abstract High-g combustor (HGC) is a significant branch of the ultra-compact combustor, an innovative gas turbine combustor with the ability to shorten the combustor length and improve engine efficiency. To improve the feasibility of the HGC concept, a new HGC was designed to substitute the conventional combustor of a KJ66 small turbine engine. The KJ66 was modified to fit an instrumentation system and test bench to conduct relative experiments. Based on the experiment results, design iterations were conducted relying on simulation methods. The design iteration was comprised of 6 primary configurations, of which the first four configurations focused on establishing an appropriate high centrifugal environment to accelerate primary combustion, while the last two modifications focused on improving overall combustion performance. In Configuration 4, a pinwheel-shaped swirl inlet was designed to successfully create the high-g environment and balance the flow distribution while bringing insignificant total pressure loss. One modification of Configuration 4 was a grid inlet design that divided the inlet channel into several sub-channels to constrain the inlet flow and establish an ideal high-g environment. The other modification was a divergent mainstream channel to encourage the dilution process and improve the exit temperature profile. The final design could save at least 1/3 of combustor length while maintaining the same level of performance as the original combustor. Further, the engine was predicted to save at least 12% of the total engine weight and improve at least 14% of the engine thrust-to-weight ratio.

scholarly journals Development Test of a Small Aero-Derived Gas Turbine Combustor for Medium Btu Gaseous Fuel

1988 ◽  
Author(s):  
Wang Hua-Fang ◽  
Liu Gao-En
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Calorific Value ◽  
Gaseous Fuel ◽  
Test Results ◽  
Gas Turbine Combustor ◽  
Heating Value ◽  
Turbine Engine ◽  
Class A ◽  
Exit Temperature

WZ-5 engine is a small aero gas turbine engine rated in 1200kw class. A development program was initiated in 1986 to develop the engine with some modifications to accommodate the medium or low Btu gaseous fuel for its industrial application. The test program was accordingly carried out for the modified engine and combustor to evaluate their ability to burn medium Btu gaseous fuel. The present investigation is a part of the program to justify whether or not the modified combustor is capable of burning the medium Btu gaseous fuel with satisfactory combustion performances. The medium Btu gaseous fuel used in the test contains 50% of H2 and 20% of CH4 and the rest of N2 as innert. That is the typical processing gas produced in chemical fertilizer production. The low heating value of the gas is 3002 kcal/nm3. All the test results whowed that when burning the medium Btu gaseous fuel the modified combustor had quite good performances except one combustor which had the injectors with slot-shape opening at the injector end and had unacceptable combustor exit temperature profile, and also showed that the modified combustor had the potential ability to burn low Btu gaseous fuel which has lower calorific value but some amount of H2.

Large-Eddy Simulation of Reacting Turbulent Flows in Complex Geometries

2005 ◽  
Vol 73 (3) ◽  
pp. 374-381 ◽  
Author(s):  
K. Mahesh ◽  
G. Constantinescu ◽  
S. Apte ◽  
G. Iaccarino ◽  
F. Ham ◽  
...  
Keyword(s):  
Large Eddy Simulation ◽  
Gas Turbine ◽  
Turbulent Flows ◽  
Reacting Flows ◽  
Gas Turbine Combustor ◽  
Turbine Engine ◽  
Progress Variable ◽  
Eddy Simulation ◽  
Variable Approach ◽  
Large Eddy

Large-eddy simulation (LES) has traditionally been restricted to fairly simple geometries. This paper discusses LES of reacting flows in geometries as complex as commercial gas turbine engine combustors. The incompressible algorithm developed by Mahesh et al. (J. Comput. Phys., 2004, 197, 215–240) is extended to the zero Mach number equations with heat release. Chemical reactions are modeled using the flamelet/progress variable approach of Pierce and Moin (J. Fluid Mech., 2004, 504, 73–97). The simulations are validated against experiment for methane-air combustion in a coaxial geometry, and jet-A surrogate/air combustion in a gas-turbine combustor geometry.

Experimental Assessment of the Emissions Benefits of a Ceramic Gas Turbine Combustor

1996 ◽  
Author(s):  
K. O. Smith ◽  
A. Fahme
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Flow Distribution ◽  
Operating Conditions ◽  
Nox Emissions ◽  
Fuel Injector ◽  
Gas Turbine Combustor ◽  
Experimental Assessment ◽  
Industrial Gas Turbine ◽  
Combustor Liner

Three subscale, cylindrical combustors were rig tested on natural gas at typical industrial gas turbine operating conditions. The intent of the testing was to determine the effect of combustor liner cooling on NOx and CO emissions. In order of decreasing liner cooling, a metal louvre-cooled combustor, a metal effusion-cooled combustor, and a backside-cooled ceramic (CFCC) combustor were evaluated. The three combustors were tested using the same lean-premixed fuel injector. Testing showed that reduced liner cooling produced lower CO emissions as reaction quenching near the liner wall was reduced. A reduction in CO emissions allows a reoptimization of the combustor air flow distribution to yield lower NOx emissions.

Effects of pulmonary edema on regional pulmonary perfusion in the intact dog lung

1980 ◽  
Vol 49 (5) ◽  
pp. 834-840 ◽  
Author(s):  
A. B. Malik ◽  
H. van der Zee ◽  
P. H. Neumann ◽  
N. B. Gertzberg
Keyword(s):  
Blood Flow ◽  
Pulmonary Edema ◽  
Pulmonary Blood Flow ◽  
Hypoxic Pulmonary Vasoconstriction ◽  
Weight Ratio ◽  
Flow Distribution ◽  
Base Line ◽  
Dependent Lung ◽  
Lung Water ◽  
Pulmonary Hemodynamics

Regional pulmonary blood flow was determined in dogs during varying degrees of pulmonary edema induced by infusing 179.2-659.4 ml/kg normal saline over 2-3 h. Pulmonary hemodynamics and regional blood flows were measured during the base-line period and at 30 min postinfusion. The degree of pulmonary edema was determined by the final extravascular lung water-to-bloodless dry lung weight ratio (W/D). In dogs developing gross alveolar edema (W/D of 10.70 +/- 0.88 vs. 3.10 +/- 0.30 in controls), the blood flow was shifted to either upper or dependent lung regions. The shift to the upper regions was associated with an increased (P < 0.05) pulmonary arterial pressure (Ppa), whereas the shift to the dependent lung was not associated with a significant change in Ppa. Breathing 100% O2 did not prevent these shifts, suggesting that they were not due to localized hypoxic pulmonary vasoconstriction. The flow distribution patterns were also not related to regional differences in edema. In contrast to the changes during fulminant edema, blood flow distribution did not change after moderate levels of pulmonary edema (W/D of 6.03 0.69), suggesting that gross alveolar flooding is required for a redistribution of pulmonary blood flow. Flow redistribution to the upper lung during airway flooding may be due to increase in Ppa, whereas the increased flow in the dependent lung during the same degree of edema may be due to "bulging" of alveolar vessels into the air spaces, secondary to a decrease in surface activity.

Assessment of the Operational Performance of Fischer-Tropsch Synthetic-Paraffinic Kerosene in a T63 Gas Turbine Compared to Conventional Jet A-1 Fuel

2009 ◽  
Author(s):  
Nigel Bester ◽  
Andy Yates
Keyword(s):  
Gas Turbine ◽  
Thermal Loading ◽  
Flame Temperature ◽  
Combustion Products ◽  
Combustion Efficiency ◽  
Efficiency Gain ◽  
Engine Efficiency ◽  
Exit Temperature ◽  
The Impact ◽  
Combustor Liner

The performance implications of operating on Synthetic-Paraffinic Kerosene (SPK) were investigated using a RR-Allison T63-A-700 Model 250-C18 B gas turbine and compared to conventional Jet A-1. The SPK was aromatic–free and possessed a greater hydrogen/carbon ratio than petroleum derived Jet A-1. The variation in aromatic content had several implications with respect to soot and NOx emissions. Reduced aromatics also implied a reduction in the radiative heat transfer to the combustor liner. A simple model was used to explore the effect of H/C ratio on the adiabatic flame temperature, the combustor exit temperature and the engine efficiency via the impact on the gas properties and these were compared to the experimental data. It was found that operation with SPK changed directionally toward improving energy extraction via a turbine and an overall efficiency gain of about 1.2% was attained with operation on SPK through increased combustion efficiency, a reduction in liner pressure loss and an improvement in the combustion products properties. A modified combustion liner was fitted to enable the thermal loading on the combustor liner to be investigated and the expected trend with the SPK fuel was confirmed and quantified.

Anchored CCD for Gas Turbine Combustor Design and Data Correlation

1997 ◽  
Vol 119 (3) ◽  
pp. 535-545 ◽  
Author(s):  
A. M. Danis ◽  
D. L. Burrus ◽  
H. C. Mongia
Keyword(s):  
Turbulent Combustion ◽  
Design Tool ◽  
Hybrid Modeling ◽  
Quality Data ◽  
Gas Turbine Combustor ◽  
Combustion Dynamics ◽  
Lean Blowout ◽  
Design Database ◽  
Exit Temperature ◽  
Temperature Levels

Correlations based on design database, combined with multidimensional computational combustion dynamics (CCD) models are used in the combustion design process. However, because of limitations in the current turbulent combustion models, numerics, and boundary conditions, CCD has provided mainly qualitative trends for aerothermal performance, emissions, and liner wall temperature levels and gradients. To overcome these deficiencies, hybrid modeling approaches have been proposed to analyze existing combustors. A typical hybrid modeling approach combines empirical and semianalytical correlations with CCD to give quantitatively accurate predictions of NOx, CO, HC, smoke, lean blowout, ignition, pattern factor, and liner wall temperatures. An alternate approach, anchored CCD, is described in this paper. First, the models were anchored with one of the five modern turbopropulsion engine combustors. The anchored models were then run for the other four combustors. The predicted results correlated well with measured NOx, CO, HC, LEO, and exit temperature quality data, demonstrating a broader applicability of the anchored method. The models were also used for designing a new combustion concept. The pretest prediction agreed well with sector rig data from development hardware, showing the feasibility of using the anchored methodology as a design tool.

A Study of External Fuel Vaporization

1981 ◽  
Author(s):  
E. J. Szetela ◽  
L. Chiappetta ◽  
C. E. Baker
Keyword(s):  
Thermal Stability ◽  
Gas Turbine ◽  
Conceptual Design ◽  
Energy Efficient ◽  
Weight Ratio ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Performance Control ◽  
Engine Thrust ◽  
Fuel Vaporization

A conceptual design study was conducted to devise and evaluate techniques for the external vaporization of fuel for use in an aircraft gas turbine with characteristics similar to the Energy Efficient Engine (E3). A second purpose of the study was to select the most favorable fuel vaporization concept. In the study, three candidate concepts were analyzed from the standpoint of fuel thermal stability, integration of the vaporizer system into the aircraft engine, engine and vaporizer dynamic response, startup and altitude restart, engine performance, control requirements, safety, and maintenance. The results of the study indicate that an external vaporization system can be devised for an E3 -type engine with hardware of reasonable size. The hardware can be packaged without increasing the total engine volume and the system is not unduly complex. The selected concept offers potential gains in engine performance in terms of reduced specific fuel consumption and improved engine thrust/weight ratio. The thrust/weight improvement can be traded against vaporization system weight. However, the vaporizer is subject to fouling with deposits formed at the walls exposed to heated fuel.

Experimental Evaluation of an Inlet Profile Generator for High-Pressure Turbine Tests

2006 ◽  
Vol 129 (2) ◽  
pp. 382-393 ◽  
Author(s):  
M. D. Barringer ◽  
K. A. Thole ◽  
M. D. Polanka
Keyword(s):  
Heat Transfer ◽  
Air Force ◽  
Flow Distribution ◽  
Turbine Engine ◽  
Turbine Inlet ◽  
Pressure Profiles ◽  
Flow Interactions ◽  
Temperature And Pressure ◽  
Inlet Conditions ◽  
Air Force Research Laboratory

Improving the performance and durability of gas turbine aircraft engines depends highly on achieving a better understanding of the flow interactions between the combustor and turbine sections. The flow exiting the combustor is very complex and it is characterized primarily by elevated turbulence and large variations in temperature and pressure. The heat transfer and aerodynamic losses that occur in the turbine passages are driven primarily by these spatial variations. To better understand these effects, the goal of this work is to benchmark an adjustable turbine inlet profile generator for the Turbine Research Facility (TRF) at the Air Force Research Laboratory. The research objective was to experimentally evaluate the performance of the nonreacting simulator that was designed to provide representative combustor exit profiles to the inlet of the TRF turbine test section. This paper discusses the verification testing that was completed to benchmark the performance of the generator. Results are presented in the form of temperature and pressure profiles as well as turbulence intensity and length scale. This study shows how a single combustor geometry can produce significantly different flow and thermal field conditions entering the turbine. Engine designers should place emphasis on obtaining accurate knowledge of the flow distribution within the combustion chamber. Turbine inlet conditions with significantly different profile shapes can result in altered flow physics that can change local aerodynamics and heat transfer.

Numerical Study of NOx Emissions in RQL Gas Turbine Combustor

2012 ◽  
Vol 510 ◽  
pp. 545-548
Author(s):  
Liang Yu ◽  
Shu Sheng Yuan ◽  
Zhi Bing Pang ◽  
Yun Liang Wang
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Numerical Study ◽  
Simple Algorithm ◽  
Wall Region ◽  
Gas Turbine Combustor ◽  
Mixing Processes ◽  
Finite Difference Equations ◽  
High Temperature Area ◽  
Exit Temperature

RNG (Renormalization Group) k-ε turbulent model was applied to the numerical simulation of turbulent mixing processes in the RQL gas turbine combustor, and SIMPLE algorithm was used to solve the finite difference equations. The calculated conclusions were used to analyze temperature distribution of the mixed flow field and near-wall region of the flow field, and then discuss the NOx emissions. The results show that the effect of the injector zone geometry and the jet to crossflow momentum flux ratios on the NOx emissions is obvious. The reasonable control of jet is beneficial to reduce the local high temperature area and is able to improve the distribution of the exit temperature. And then achieve the goal of reducing the environmental pollution.

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