scholarly journals A Compact, Intercooled and Regenerated Gas Turbine for HALE Applications

1992 ◽  
Author(s):  
Jennifer J. Kolden ◽  
William J. Bigbee-Hansen ◽  
Donald G. Iverson
Keyword(s):  
Total Energy ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Optimization Technique ◽  
Specific Fuel Consumption ◽  
Optimization Process ◽  
Turbine Engine ◽  
Installation Effects ◽  
Long Endurance ◽  
The Impact

A mechanically coupled, two spool, intercooled and regenerated gas turbine engine designed for a high altitude, long endurance (HALE) mission is described. The design philosophy was based on minimization of total energy expended using a two stage optimization process utilizing a multivariate regression and optimization technique. This optimization process addressed the impact of the propulsion system as installed on an air vehicle, including all installation effects. Weight and drag of the complete nacelle as they were affected by the characteristics of the engine was included. A brake specific fuel consumption (BSFC) of 0.262 lb/hr/hp (0.159 kg/hr/kw) and mission average specific fuel consumption (MSFC) of 0.266 lb/hp-hr (0.160 kg/kW-hr) was estimated for the bare engine and an MSFC of 0.327 lb/hp-hr (0.199 kg/kW-hr) was estimated for the fully installed engine, including the nacelle drag penalty, where MSFC is defined as the total fuel required to complete the mission divided by the total energy expended during the mission. A comparison with other gas turbine and reciprocating engines currently considered as candidates for HALE applications is also presented.

scholarly journals Wave-Rotor-Enhanced Gas Turbine Engines

1997 ◽  
Vol 119 (2) ◽  
pp. 469-477 ◽  
Author(s):  
G. E. Welch ◽  
S. M. Jones ◽  
D. E. Paxson
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Engine Performance ◽  
Specific Fuel Consumption ◽  
Specific Power ◽  
Inlet Temperature ◽  
Wave Rotor ◽  
Performance Levels ◽  
Turbine Engine ◽  
The Impact

The benefits of wave rotor topping in small (300- to 500-kW [400- to 700-hp] class) and intermediate (2000- to 3000-kw [3000- to 4000-hp] class) turboshaft engines, and large (350- to 450-kN [80,000- to 100,000-lbf] class) high-bypass-ratio turbofan engines are evaluated. Wave rotor performance levels are calculated using a one-dimensional design/analysis code. Baseline and wave-rotor-enhanced engine performance levels are obtained from a cycle deck in which the wave rotor is represented as a burner with pressure gain. Wave rotor topping is shown to enhance the specific fuel consumption and specific power of small- and intermediate-sized turboshaft engines significantly. The specific fuel consumption of the wave-rotor-enhanced large turbofan engine can be reduced while it operates at a significantly reduced turbine inlet temperature. The wave-rotor-enhanced engine is shown to behave off-design like a conventional engine. Discussion concerning the impact of the wave rotor/gas turbine engine integration identifies technical challenges.

Performance and Emission Characteristics of a Small Scale Gas Turbine Engine Fueled With Propanol/Jet A Blends

2011 ◽  
Author(s):  
Carlos J. Mendez ◽  
Ramkumar N. Parthasarathy ◽  
Subramanyam R. Gollahalli
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbine Engine ◽  
Single Stage ◽  
Specific Fuel Consumption ◽  
Small Scale ◽  
Emission Characteristics ◽  
Turbine Engine ◽  
Performance And Emission ◽  
Emission Index

Alcohols serve as an alternate energy resource to the conventional petroleum-based fuels. The objective of this study was to document the performance and emission characteristics of blends of n-propanol and Jet A fuel in a small-scale gas turbine engine. The experiments were conducted in a 30kW gas turbine engine with a single-stage centrifugal flow compressor, annular combustion chamber and a single-stage axial flow turbine. In addition to neat propanol and Jet A fuel, three blends, with 25%, 50% and 75% of propanol by volume, were used as the fuels. The thrust, thrust-specific fuel consumption, and the concentrations of CO and NOx in the exhaust were measured and compared with those measured with Jet A fuel. The engine was operated at the same throttle settings with all the fuels. The operational range of engine rotational speed was shifted downwards with the addition of propanol due to its lower heating value. The thrust specific fuel consumption increased with the addition of propanol, while the CO emission index increased and NOx emission index decreased.

Comparative Energy and Exergy Analysis of Proposed Gas Turbine Cycle With Simple Gas Turbine Cycle at Same Operational Cost

2019 ◽  
Author(s):  
M. N. Khan ◽  
Ibrahim M. Alarifi ◽  
I. Tlili
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Exergy Analysis ◽  
Pressure Ratio ◽  
Specific Fuel Consumption ◽  
Exergy Destruction ◽  
Energy And Exergy ◽  
Energy And Exergy Analysis ◽  
Gas Turbine Cycle ◽  
The Impact

Abstract Environmentally friendly and effective power systems have been receiving increased investigation due to the aim of addressing global warming, energy expansion, and economic growth. Gas turbine cycles are perceived as a useful technology that has advanced power capacity. In this research, a gas turbine cycle has been proposed and developed from a simple and regenerative gas turbine cycle to enhance performance and reduce Specific fuel consumption. The impact of specific factors regarding the proposed gas turbine cycle on thermal efficiency, net output, specific fuel consumption, and exergy destruction, have been inspected. The assessments of the pertinent parameters were performed based on conventional thermodynamic energy and exergy analysis. The results obtained indicate that the peak temperature of the Proposed Gas Turbine Cycle increased considerably without affecting fuel consumption. The results show that at Pressure Ratio (rp = 6) the performance of the Proposed Gas Turbine Cycle is much better than Single Gas Turbine Cycle but the total exergy destruction of Proposed Gas Turbine Cycle higher than the SGTC.

scholarly journals Performance Improvement of a 43 MW Class Gas Turbine Engine with Inlet Air Cooling

2021 ◽  
Vol 9 (5) ◽  
pp. 539-544
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbine Engine ◽  
Specific Fuel Consumption ◽  
Coefficient Of Performance ◽  
Air Cooling ◽  
Climate Conditions ◽  
Turbine Engine ◽  
Hot Climate ◽  
Fuel Consumption Improvement

In this study, a process of inlet air cooling was implemented in the intake of a land-based gas turbine engine for electricity generation. The motivation behind the study is to improve the performance of the gas turbine engine in hot climate conditions,which causes a significant decrease in the output power and an increase in specific fuel consumption. For inlet air cooling, a refrigeration cycle was attached to the turbo-shaft gas turbine engine,and power required by the refrigeration is extracted from the mechanical engine power output of the gas turbine. A 43 MWclass gas turbine engine which is similar totheGeneral Electric LM6000 engine was modeled in this study. Considering an average coefficient of performance of 3.0 for a refrigeration system, the inlet cooling provided (by supplying cooled inlet air at 15oC) a 22.21% net power increase anda5.2% power specific fuel consumption improvement at 55oCambient conditions.

scholarly journals Mathematical model for calculating the mass of a heat exchanger in problems of optimizing the parameters of the working process of aircraft gas turbine engines

2019 ◽  
Vol 18 (3) ◽  
pp. 67-80
Author(s):  
V. S. Kuz'michev ◽  
H. Omar ◽  
A. Yu. Tkachenko ◽  
A. A. Bobrik
Keyword(s):  
Mathematical Model ◽  
Heat Exchanger ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Heat Recovery ◽  
Specific Weight ◽  
Specific Fuel Consumption ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine

Despite the fact that aviation gas turbine engines (GTE) have reached a high degree of sophistication, requirements for the improvement of their efficiency are constantly increasing. Reduction of specific fuel consumption and specific weight of the engine unit makes it possible to improve aircraft performance. One of the effective means of reducing specific fuel consumption and obtaining high thermal efficiency of a gas turbine engine is the use of heat recovery, so the interest in it holds throughout the period of development of gas turbine engines. However, the use of heat recovery in aircraft gas turbine engines is faced with a contradiction: on the one hand, heat recovery allows reducing specific fuel consumption, but, on the other hand, it increases the weight of the power plant due to the presence of a heat exchanger. Moreover, with the increase in the degree of regeneration, specific fuel consumption decreases, whereas the mass of the power plant increases.To obtain the desired effect, it is necessary to optimize simultaneously both the parameters of the engine work process and the degree of regeneration of the heat exchanger according to the criteria of evaluating the engine unit in the aircraft system. For this purpose, it is necessary to have a mathematical model for estimating the weight of a highly efficient aircraft heat exchanger. The article presents a developed mathematical model for calculating the weight of a compact plate heat exchanger used to increase the efficiency of a gas turbine engine due to the heating of compressed air entering the combustion chamber by the hot gas that enters the combustion chamber from behind the turbine. We chose a rational pattern of relative motion of the working media in the heat exchanger, the optimal type of plate-type heat transfer surface in terms of minimizing the weight of the heat exchanger and the hydraulic losses in the air and gas ducts. For the selected surface type, the dependence of the specific weight of the heat exchanger on the degree of regeneration is determined for different nozzle exhaust velocities on the basis of a computational algorithm. To assess the reliability of the obtained model, comparative analysis of the effect of the degree of regeneration on the specific weight of the heat exchanger was carried out, based on the comparison of the results of calculations for the developed model with the data of other authors and with the data for the produced regenerators.

Development of a Centrifugal Compressor for a Small Gas-Turbine Engine

1956 ◽  
Author(s):  
N. R. Balling ◽  
V. W. van Ornum
Keyword(s):  
Research And Development ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Specific Fuel Consumption ◽  
General Description ◽  
Turbine Engine

The objective of the research and development program reported by this paper was to decrease the specific fuel consumption of a small gas-turbine engine by means of an increase in pressure ratio alone. Development of a centrifugal compressor is presented, with a general description of equipment, methods, and special problems met during the tests. Results showed the required decrease in specific fuel consumption and pointed up the advantages of a straightforward development program.

Account of Film Turbulence for Predicting Film Cooling Effectiveness in Gas Turbine Combustors

1979 ◽  
Author(s):  
G. J. Sturgess
Keyword(s):  
Gas Turbine ◽  
Film Cooling ◽  
Cooling Effectiveness ◽  
Turbine Engine ◽  
Film Cooling Effectiveness ◽  
Wide Range ◽  
Engine Combustion ◽  
Turbulence Effects ◽  
The Impact ◽  
Combustor Liner

The paper deals with a small but important part of the overall gas turbine engine combustion system and continues earlier published work on turbulence effects in film cooling to cover the case of film turbulence. Film cooling of the gas turbine combustor liner imposes certain geometric limitations on the coolant injection device. The impact of practical film injection geometry on the cooling is one of increased rates of film decay when compared to the performance from idealized injection geometries at similar injection conditions. It is important to combustor durability and life estimation to be able to predict accurately the performance obtainable from a given practical slot. The coolant film is modeled as three distinct regions, and the effects of injection slot geometry on the development of each region are described in terms of film turbulence intensity and initial circumferential non-uniformity of the injected coolant. The concept of the well-designed slot is introduced and film effectiveness is shown to be dependent on it. Only slots which can be described as well-designed are of interest in practical equipment design. A prediction procedure is provided for well-designed slots which describes growth of the film downstream of the first of the three film regions. Comparisons of predictions with measured data are made for several very different well-designed slots over a relatively wide range of injection conditions, and good agreement is shown.

scholarly journals Advanced Turboprop Engines for Long Endurance Naval Patrol Aircraft

1982 ◽  
Author(s):  
R. Hirschkron ◽  
R. H. Davis
Keyword(s):  
Pressure Drop ◽  
Fuel Consumption ◽  
Pressure Ratio ◽  
Specific Fuel Consumption ◽  
Performance Requirements ◽  
The Future ◽  
Weight Design ◽  
Long Endurance

Long endurance naval patrol aircraft of the future will require more efficient advanced turboprop powerplants. Engines used in this kind of application will have performance requirements emphasizing prolonged endurance and very low specific fuel consumption for cruise and part-power loiter operation. Regenerative, regenerative/intercooled and advanced conventional cycle screening studies were carried out to select the cycle pressure ratio and turbine temperature for each type, considering the effects on installed performance and weight. Design and cycle choices were studied in each engine category including recuperator types, effectiveness, pressure drop, bypass bleed and variable area turbine nozzle. The engine characteristics of each type were then compared using a representative mission. The advanced conventional engine showed the largest potential, the regenerative second and the regenerative/intercooled the least promise for lower installed fuel consumption and improved mission performance.

Rolls Royce/Allison 501-K Gas Turbine Anti-Fouling Compressor Coatings Evaluation

2002 ◽  
Author(s):  
Daniel E. Caguiat
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbines ◽  
Performance Degradation ◽  
Specific Fuel Consumption ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Inlet ◽  
Compressor Performance ◽  
Compressor Efficiency

The Naval Surface Warfare Center, Carderock Division (NSWCCD) Gas Turbine Emerging Technologies Code 9334 was tasked by NSWCCD Shipboard Energy Office Code 859 to research and evaluate fouling resistant compressor coatings for Rolls Royce Allison 501-K Series gas turbines. The objective of these tests was to investigate the feasibility of reducing the rate of compressor fouling degradation and associated rate of specific fuel consumption (SFC) increase through the application of anti-fouling coatings. Code 9334 conducted a market investigation and selected coatings that best fit the test objective. The coatings selected were Sermalon for compressor stages 1 and 2 and Sermaflow S4000 for the remaining 12 compressor stages. Both coatings are manufactured by Sermatech International, are intended to substantially decrease blade surface roughness, have inert top layers, and contain an anti-corrosive aluminum-ceramic base coat. Sermalon contains a Polytetrafluoroethylene (PTFE) topcoat, a substance similar to Teflon, for added fouling resistance. Tests were conducted at the Philadelphia Land Based Engineering Site (LBES). Testing was first performed on the existing LBES 501-K17 gas turbine, which had a non-coated compressor. The compressor was then replaced by a coated compressor and the test was repeated. The test plan consisted of injecting a known amount of salt solution into the gas turbine inlet while gathering compressor performance degradation and fuel economy data for 0, 500, 1000, and 1250 KW generator load levels. This method facilitated a direct comparison of compressor degradation trends for the coated and non-coated compressors operating with the same turbine section, thereby reducing the number of variables involved. The collected data for turbine inlet, temperature, compressor efficiency, and fuel consumption were plotted as a percentage of the baseline conditions for each compressor. The results of each plot show a decrease in the rates of compressor degradation and SFC increase for the coated compressor compared to the non-coated compressor. Overall test results show that it is feasible to utilize anti-fouling compressor coatings to reduce the rate of specific fuel consumption increase associated with compressor performance degradation.

LV100 AIPS Technology—For Future Army Propulsion

1992 ◽  
Author(s):  
Walter Brockett ◽  
Angelo Koschier
Keyword(s):  
Control Systems ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Cooling System ◽  
Gas Turbine Engine ◽  
Air Filtration ◽  
Turbine Engine ◽  
Overall Design ◽  
Armored Vehicle ◽  
And Control

The overall design of and Advanced Integrated Propulsion System (AIPS), powered by an LV100 gas turbine engine, is presented along with major test accomplishments. AIPS was a demonstrator program that included design, fabrication, and test of an advanced rear drive powerpack for application in a future heavy armored vehicle (54.4 tonnes gross weight). The AIPS design achieved significant improvements in volume, performance, fuel consumption, reliability/durability, weight and signature reduction. Major components of AIPS included the recuperated LV100 turbine engine, a hydrokinetic transmission, final drives, self-cleaning air filtration (SCAF), cooling system, signature reduction systems, electrical and hydraulic components, and control systems with diagnostics/prognostics and maintainability features.

Sign in / Sign up

Export Citation Format

Share Document