Gas Turbine With Intermediate Heat Exchanger for Flight Application

1990 ◽  
Author(s):  
J. Shapiro ◽  
A. Levy
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
High Power ◽  
Fuel Economy ◽  
Weight Ratio ◽  
Power Weight ◽  
Turbine Engine ◽  
Additional Weight ◽  
Intermediate Heat Exchanger ◽  
Turbine Design

High power/weight ratio and low SFC are the most important requirements for an airborne engine. This may be achieved by a gas turbine engine with an intermediate heat exchanger, combined with a double-decked compressor-turbine design. In this engine, the specific fuel consumption is minimal at 70% of maximum power output for best fuel economy in helicopter engines. The additional weight, due to its design, is compensated by fuel saved in less than one hour flight for a 926 kW cruise power engine.

Gas Turbine Recuperator Technology Advancements

1972 ◽  
Author(s):  
C. F. McDonald
Keyword(s):  
Heat Exchanger ◽  
Power Systems ◽  
Gas Turbine ◽  
Substantial Reduction ◽  
Liquid Fuels ◽  
Cycle Space ◽  
Fuel Savings ◽  
Efficient Heat Transfer ◽  
The Cost ◽  
Turbine Design

Because of intense development in the aircraft gas turbine field over the last 30 years, the fixed boundary recuperator has received much less development attention than the turbomachinery, and is still proving to be the nemesis of the small gas turbine design engineer. For operation on cheap fuel, such as natural gas, the simple cycle-engine is the obvious choice, but where more expensive liquid fuels are to be burned, the economics of gas turbine operation can be substantially improved by incorporating an efficient, reliable recuperator. For many industrial, vehicular, marine, and utility applications it can be shown that the gas turbine is a more attractive prime mover than either the diesel engine or steam turbine. For some military applications the fuel logistics situation shows the recuperative gas turbine to be the most effective power plant. For small nuclear Brayton cycle space power systems the recuperator is an essential component for high overall plant efficiency, and hence reduced thermal rejection to the environment. Data are presented to show that utilization of compact efficient heat transfer surfaces developed primarily for aerospace heat exchangers, can result in a substantial reduction in weight and volume, for industrial, vehicular, marine, and nuclear gas turbine recuperators. With the increase in overall efficiency of the recuperative cycle (depending on the level of thermal effectiveness, and the size and type of plant), the cost of the heat exchanger can often be paid for in fuel savings, after only a few hundred hours of operation. Heat exchanger surface geometries and fabrication techniques, together with specific recuperator sizes for different applications, are presented. Design, performance, structural, manufacturing, and economic aspects of compact heat exchanger technology, as applied to the gas turbine, are discussed in detail, together with projected future trends in this field.

Future Vehicular Recuperator Technology Projections

1994 ◽  
Author(s):  
Robert A. Wilson ◽  
Daniel B. Kupratis ◽  
Satyanarayana Kodali
Keyword(s):  
Gas Turbine ◽  
Fuel Economy ◽  
Department Of Defense ◽  
Gas Turbines ◽  
High Performance ◽  
Development Program ◽  
Turn Of The Century ◽  
Turbine Engine ◽  
Technology Roadmap ◽  
Vehicle Propulsion

The Department of Defense and NASA have funded a major gas turbine development program, Integrated High Performance Turbine Engine Technology (IHPTET), to double the power density and fuel economy of gas turbines by the turn of the century. Seven major US gas turbine developers participated in this program. While the focus of IHPTET activity has been aircraft propulsion, the same underlying technology can be applied to water craft and terrestrial vehicle propulsion applications, such as the future main battle tank. For these applications, the gas turbines must be equipped with recuperators. Currently, there is no technology roadmap or set of goals to guide industry and government in the development of a next generation recuperator for such applications.

scholarly journals The effect of heat recovery on the optimal values of helicopter turboshaft engine parameters

2020 ◽  
Vol 19 (4) ◽  
pp. 43-57
Author(s):  
H. H. Omar ◽  
V. S. Kuz'michev ◽  
A. O. Zagrebelnyi ◽  
V. A. Grigoriev
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
Heat Recovery ◽  
Thermodynamic Cycle ◽  
Gas Turbine Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Working Process ◽  
Turbine Engine ◽  
Recuperative Heat Exchanger

Recent studies related to fuel economy in air transport conducted in our country and abroad show that the use of recuperative heat exchangers in aviation gas turbine engines can significantly, by up to 20...30%, reduce fuel consumption. Until recently, the use of cycles with heat recovery in aircraft gas turbine engines was restrained by a significant increase in the mass of the power plant due to the installation of a heat exchanger. Currently, there is a technological opportunity to create compact, light, high-efficiency heat exchangers for use on aircraft without compromising their performance. An important target in the design of engines with heat recovery is to select the parameters of the working process that provide maximum efficiency of the aircraft system. The article focused on setting of the optimization problem and the choice of rational parameters of the thermodynamic cycle parameters of a gas turbine engine with a recuperative heat exchanger. On the basis of the developed method of multi-criteria optimization the optimization of thermodynamic cycle parameters of a helicopter gas turbine engine with a ANSAT recuperative heat exchanger was carried out by means of numerical simulations according to such criteria as the total weight of the engine and fuel required for the flight, the specific fuel consumption of the aircraft for a ton- kilometer of the payload. The results of the optimization are presented in the article. The calculation of engine efficiency indicators was carried out on the basis of modeling the flight cycle of the helicopter, taking into account its aerodynamic characteristics. The developed mathematical model for calculating the mass of a compact heat exchanger, designed to solve optimization problems at the stage of conceptual design of the engine and simulation of the transport helicopter flight cycle is presented. The developed methods and models are implemented in the ASTRA program. It is shown that optimal parameters of the working process of a gas turbine engine with a free turbine and a recuperative heat exchanger depend significantly on the heat exchanger effectiveness. The possibility of increasing the efficiency of the engine due to heat regeneration is also shown.

Feasibility Study of a Radical Vane-Integrated Heat Exchanger for Turbofan Engine Applications

2020 ◽  
Author(s):  
Isak Jonsson ◽  
Carlos Xisto ◽  
Hamidreza Abedi ◽  
Tomas Grönstedt ◽  
Marcus Lejon
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
Conceptual Design ◽  
Feasibility Study ◽  
Compact Heat Exchanger ◽  
Turbofan Engine ◽  
Turbine Engine ◽  
Compression System ◽  
Last Stage ◽  
Pressure Compressor

Abstract In the present study, a compact heat exchanger for cryogenically fueled gas turbine engine applications is introduced. The proposed concept can be integrated into one or various vanes that comprise the compression system and uses the existing vane surface to reject core heat to the cryogenic fuel. The requirements for the heat exchanger are defined for a large geared-turbofan engine operating on liquid hydrogen. The resulting preliminary conceptual design is integrated into a modified interconnecting duct and connected to the last stage of a publicly available low-pressure compressor geometry. The feasibility of different designs is investigated numerically, providing a first insight on the parameters that govern the design of such a component.

1000 Hour Qualification Test of the Textron Lycoming TF40B Marine Gas Turbine Engine for the U.S. Navy LCAC Craft

1988 ◽  
Author(s):  
Michael J. Zoccoli
Keyword(s):  
Gas Turbine ◽  
High Power ◽  
Duty Cycle ◽  
Development Program ◽  
Continuous Operation ◽  
Qualification Test ◽  
Turbine Engine ◽  
Qualification Testing ◽  
Carbon Erosion ◽  
The U.S

This paper describes the qualification testing of the TF40B marine gas turbine in accordance with the duty cycle as specified in MIL-E-17341C, but with modifications that reflect the specific engine application to the U.S. Navy LCAC vehicle. Among the particular requirements of the 1000 hour test are continuous operation in a salt-laden environment of given concentration and humidity, and frequent shutdowns from relatively high power with an ensuing soakback interval. The narrative discusses the method of test, the duty cycle, and the results which were obtained. In an epilogue which focuses on posttest activities, a description is given of the corrective actions taken to resolve certain problems that arose during the course of the test. One such problem, namely the occurrence of carbon erosion upon certain hot section components, was eliminated by modification to the combustor, in a very successful posttest test development program.

Regenerator Development for the British Leyland 2S/350/R Gas Turbine Engine

1974 ◽  
Author(s):  
J. A. Ritchie ◽  
P. A. Phillips ◽  
M. C. S. Barnard
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Single Disk

This paper describes the application of the ceramic regenerator to the British Leyland truck gas turbine. Aspects of mounting, driving and sealing the heat exchanger disk are covered with particular reference to the single disk version of the 2S/350/R engine.

Fabrication and Performance of a Pin Fin Micro Heat Exchanger

2004 ◽  
Vol 126 (3) ◽  
pp. 434-444 ◽  
Author(s):  
Christophe Marques ◽  
Kevin W. Kelly
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
Heat Exchangers ◽  
Turbine Blades ◽  
High Heat ◽  
Gas Turbine Engine ◽  
High Heat Flux ◽  
Turbine Engine ◽  
Pin Fin ◽  
Micro Heat Exchanger

Nickel micro pin fin heat exchangers can be electroplated directly onto planar or non-planar metal surfaces using a derivative of the LIGA micromachining process. These heat exchangers offer the potential to more effectively control the temperature of surfaces in high heat flux applications. Of particular interest is the temperature control of gas turbine engine components. The components in the gas turbine engine that require efficient, improved cooling schemes include the gas turbine blades, the stator vanes, the turbine disk, and the combustor liner. Efficient heating of component surfaces may also be required (i.e., surfaces near the compressor inlet to prevent deicing). In all cases, correlations providing the Nusselt number and the friction factor are needed for such micro pin fin heat exchangers. Heat transfer and pressure loss experimental results are reported for a flat parallel plate pin fin micro heat exchanger with a staggered pin fin array, with height-to-diameter ratios of 1.0, with spacing-to-diameter ratios of 2.5 and for Reynolds numbers (based on the hydraulic diameter of the channel) from 4000 to 20,000. The results are compared to studies of larger scale, but geometrically similar, pin fin heat exchangers. To motivate further research, an analytic model is described which uses the empirical results from the pin fin heat exchanger experiments to predict a cooling effectiveness exceeding 0.82 in a gas turbine blade cooling application. As a final point, the feasibility of fabricating a relatively complex micro heat exchanger on a simple airfoil (a cylinder) is demonstrated.

Paper 16: Case for the Single-Shaft Vehicular Gas Turbine Engine

1968 ◽  
Vol 183 (14) ◽  
pp. 156-176 ◽  
Author(s):  
A. F. McLean
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Fuel Economy ◽  
Lower Cost ◽  
Turbine Engine ◽  
Advantages And Disadvantages ◽  
Initial Cost ◽  
Variable Transmission ◽  
Infinitely Variable Transmission

This paper reviews gas turbine cycles most favoured for vehicular use. It suggests the single-shaft turbine engine as a possible contender for a lower cost approach, where fuel economy requirements are not met by complexity of cycle but by operation at higher turbine inlet temperatures. The question, ‘Where does the engine end and the transmission begin?’ is discussed, and an example of an infinitely variable transmission is explored as a means for overcoming the performance deficiencies of the single-shaft machine. The paper examines the advantages and disadvantages of this type of turbine engine with respect to acceleration and torque characteristics, fuel consumption, engine braking, initial cost, and design for simplicity and high temperature.

Conversion of the AE 1107C From the V-22 Osprey Application to Marine Service

2013 ◽  
Author(s):  
Zechariah D. Green ◽  
Sean Padfield ◽  
Andrew F. Barrett ◽  
Paul G. Jones
Keyword(s):  
Gas Turbine ◽  
System Integration ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Naval Vessel ◽  
Turbine Engine ◽  
The Us ◽  
Technical Risk ◽  
Turbine Design ◽  
System Designs

This paper presents a study on the conversion of the Rolls-Royce AE 1107C V-22 Osprey gas turbine engine into the MT7 Ship-to-Shore Connector (SSC) marine gas turbine engine. The US Navy led SSC design requires a propulsion and lift gas turbine rated at 5,230 shaft horsepower, which the AE 1107C variant MT7 is capable of providing with margin on power and specific fuel consumption. The MT7 leverages the AE family of engines to provide a propulsion and lift engine solution for the SSC craft. Extensive testing and analysis completed during the AE 1107C development program aided in the robust gas turbine design required to meet the needs of the SSC program. Requirements not met by the AE 1107C configuration were achieved with designs based on the AE family of engines and marine grade sub-system designs. Despite the fact that system integration and testing remain as key activities for integrating the MT7 with the SSC craft, conversion of the AE 1107C FAA certified engine into an American Bureau of Shipping Naval Vessel Rules Type Approved MT7 engine provides a low technical risk alternative for the demanding requirements of the SSC application.

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