Optimization Design Analysis of Primary Surface Recuperator for Rotorcraft Powerplant Applications

2019 ◽  
Author(s):  
Chengyu Zhang ◽  
Volker Gümmer
Keyword(s):  
Genetic Algorithm ◽  
Pressure Drop ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Optimization Design ◽  
Shape Parameters ◽  
Aero Engine ◽  
Calculation Results ◽  
Aero Engines ◽  
Surface Plate

Abstract The growing demand for highly efficient, environmentally friendly aero-engines highlights the incorporation of recuperators into gas turbine systems, which is especially attractive for rotorcraft powerplants, as the majority of their mission time is spent at part load cruise power (typically above 60%) with the non-optimum specific fuel consumption (SFC) characteristic. In this work, a primary surface recuperator (PSR) for the 300kW-class rotorcraft powerplant is considered for optimization by using a Genetic Algorithm (GA). By the very nature of aero-engines application, two different objective optimizations are conducted, aimed at minimizing the recuperator weight or/and reducing pressure drop, maximizing recuperator effectiveness. The geometries of the surface plate remain constant, while three shape parameters work as variables for defined constraints. The optimization process proves that GA is an adequate tool in recuperator design optimization according to the specified objectives. Based on calculation results, potential recuperator designs for aero-engine application are suggested.

Thermodynamics Cycle Analysis, Pressure Loss and Heat Transfer Assessment of a Recuperative System for Aero Engines

2014 ◽  
Author(s):  
A. Goulas ◽  
S. Donnerhack ◽  
M. Flouros ◽  
D. Misirlis ◽  
Z. Vlahostergios ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Fuel Consumption ◽  
Heat Exchangers ◽  
Engine Performance ◽  
Specific Fuel Consumption ◽  
Hot Gas ◽  
Research Activities ◽  
Aero Engine ◽  
Overall Efficiency ◽  
Aero Engines

Aiming in the direction of designing more efficient aero engines, various concepts have been developed in recent years, among which is the concept of an intercooled and recuperative aero engine. Particularly in the area of recuperation, MTU Aero Engines has been driving research activities in the last decade. This concept is based on the use of a system of heat exchangers mounted inside the hot-gas exhaust nozzle (recuperator). Through the operation of the system of heat exchangers, the heat from the exhaust gas, downstream the LP turbine of the jet engine is driven back to the combustion chamber. Thus, the preheated air enters the engine combustion chamber with increased enthalpy, providing improved combustion and by consequence, increased fuel economy and low-level emissions. If additionally an intercooler is placed between the compressor stages of the aero engine, the compressed air is then cooled by the intercooler thus, less compression work is required to reach the compressor target pressure. In this paper an overall assessment of the system is presented with particular focus on the recuperative system and the heat exchangers mounted into the aero engine’s exhaust nozzle. The herein presented results were based on the combined use of CFD computations, experimental measurements and thermodynamic cycle analysis. They focus on the effects of total pressure losses and heat exchanger efficiency on the aero engine performance especially the engine’s overall efficiency and the specific fuel consumption. More specifically, two different hot-gas exhaust nozzle configurations incorporating modifications in the system of heat exchangers are examined. The results show that significant improvements can be achieved in overall efficiency and specific fuel consumption hence contributing into the reduction of CO2 and NOx emissions. The design of a more sophisticated recuperation system can lead to further improvements in the aero engine efficiency in the reduction of fuel consumption. This work is part of the European funded research program LEMCOTEC (Low Emissions Core engine Technologies).

scholarly journals A scientometric analysis and critical review of gas turbine aero-engines control: From Whittle engine to more-electric propulsion

2020 ◽  
pp. 002029402095667
Author(s):  
Seyed Jalal Mohammadi ◽  
Seyed Alireza Miran Fashandi ◽  
Soheil Jafari ◽  
Theoklis Nikolaidis
Keyword(s):  
Control Systems ◽  
Gas Turbine ◽  
Carbon Dioxide Emissions ◽  
Electric Propulsion ◽  
Control Algorithms ◽  
Scientometric Analysis ◽  
Engine Control ◽  
Advantages And Disadvantages ◽  
Aero Engine ◽  
Aero Engines

The gas turbine aero-engine control systems over the past eight decades have been thoroughly investigated. This review purposes are to present a comprehensive reference for aero-engine control design and development based on a systematic scientometric analysis and to categorize different methods, algorithms, and approaches taken into account to improve the performance and operability of aircraft engines from the first days to present to enable this challenging technology to be adopted by aero-engine manufacturers. Initially, the benefits of the control systems are restated in terms of improved engine efficiency, reduced carbon dioxide emissions, and improved fuel economy. This is followed by a historical coverage of the proposed concepts dating back to 1936. A comprehensive scientometric analysis is then presented to introduce the main milestones in aero-engines control. Possible control strategies and concepts are classified into four distinct phases, including Single input- single output control algorithms, MIN-MAX or Cascade control algorithms, advanced control algorithms, More-electric and electronic control algorithms and critically reviewed. The advantages and disadvantages of milestones are discussed to cover all practical aspects of the review to enable the researchers to identify the current challenges in aircraft engine control systems.

Structural Integrity Validation for Rotor Discs and Shafts in Aero-Engines

2013 ◽  
Author(s):  
Sanju Kumar ◽  
Rashmi Rao ◽  
Rajeevalochanam B. Ananthappa ◽  
Venkateshwarlu Mogullapally
Keyword(s):  
Gas Turbine ◽  
Material Characterization ◽  
Structural Integrity ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Aero Engine ◽  
Aero Engines ◽  
Integrity Analysis ◽  
Structural Validation ◽  
Validation Testing

Design of rotating structures in military gas turbine engine is complex and arduous. The aero engine main discs and shafts are designed to achieve maximum operating capabilities under severe loads. The potential failures of primary rotating parts are extremely catastrophic. Hence, ignoring structural integrity aspects, results in engine failures, which is a major concern and motivation for the present paper. In this paper structural integrity analysis using CAE are discussed for rotating components and various structural validation testing employed are highlighted. The structural integrity study carried out conforms to stipulation of MIL 5007 D/E. The validation carried out includes material characterization, cyclic spin tests, overspeed and burst speed tests. This paper also emphasizes structural integrity studies on engine main shafts, for buckling, maneuvers and blade-off loads.

scholarly journals Analysis of Ambient Temperature Effect on Gas Turbine Centaur 40 at Sepinggan Production Field, Chevron Indonesia Company

2019 ◽  
Vol 3 (2) ◽  
pp. 29
Author(s):  
Muhammad Adib
Keyword(s):  
Ambient Temperature ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Thermal Efficiency ◽  
Gas Flow ◽  
Specific Fuel Consumption ◽  
Ambient Temperatures ◽  
Optimal Output ◽  
Power Turbine ◽  
Calculation Results

               Gas turbine Centaur 40 drive gas compressor operates 24 hours a day and continuously with monitored output parameters, namely pressure and the gas flow capacity In its operation, it is often found that the optimal output parameters are generated during low ambient temperatures, for example in the night, cloudy and rainy. This study is aimed to determine the effect of changes in ambient temperature on the gas turbine power. During operation and research was done, the independent variable used is ambient temperature at 24 – 33 0C at constant 100% rotation of the turbine shaft. The decrease in gas turbine performance is seen from the increase in Specific Fuel Consumption (SFC), a decrease in the power produced and thermal efficiency. Specific fuel consumption value from the calculation results is 0.06072 kg/kW.h at 24 0C ambient temperature and 0.06565 kg/kW.h at 33 0C ambient temperature. Power produced by the power turbine is 3532,657 HP at 24 0C ambient temperature and 3046,557 HP at 33 0C ambient temperature, while the thermal efficiency cycle is 54,159% at 24 0C ambient temperature and 49,727% at 33 0C ambient temperature. Keywords: gas turbine, ambient temperature, specific fuel consumption, thermal efficiency.

Optimization of Advanced Cycle Gas Turbine Intercooler Structure Based on Genetic Algorithm

2011 ◽  
Vol 317-319 ◽  
pp. 2041-2046
Author(s):  
Zhi Tao Wang ◽  
Shu Ying Li ◽  
Ping Ping Luo
Keyword(s):  
Heat Transfer ◽  
Genetic Algorithm ◽  
Heat Exchanger ◽  
Pressure Drop ◽  
Gas Turbine ◽  
Thermal Efficiency ◽  
Heat Load ◽  
Structure Parameters ◽  
Heat Transfer Efficiency

As an important component of intercooled cycle gas turbine, intercooler directly affects the ratio power, thermal efficiency and various situation quality of gas turbine system. In this paper, efficiency-heat transfer units were used for the design of intercooler, and the structure parameters were optimized by genetic algorithm. The optimization results show that under the condition of required heat load and allowable pressure drop, the heat exchanger can be guaranteed as the smaller weight and the larger heat transfer efficiency, which can offer reference for the design of the actual intercooler.

Air-Cooled Engines in Service

1929 ◽  
Vol 33 (220) ◽  
pp. 269-318
Author(s):  
A. H. R. Fedden
Keyword(s):  
Fuel Consumption ◽  
The Sun ◽  
Oil Consumption ◽  
Missionary Work ◽  
The Past ◽  
New Family ◽  
Aero Engine ◽  
Aero Engines ◽  
The Way

It is now rather more than three years since I last had the honour of presenting a paper before this Society dealing with air-cooled aero engines. At that time the air-cooled engine had not fully won a place “in the sun,” which may be fairly stated to be the case to-day.For some years after the war there was a considerable aversion towards the air-cooled aero engine owing to certain types which had been developed during the war which were supposedly air-cooled, but in reality obtained the greater portion of their cooling by means of exorbitant fuel and oil consumption. As lately as four years ago the practical advantages of the air-cooled engine were only tentatively appreciated by the aircraft constructor, and naturally, owing to his somewhat painful experiences in the past in respect of unreliability and high fuel consumption; it required some missionary work and proof in order to persuade him that the new family of air-cooled engines would really perform in the way their designers claimed for them.

Development, Numerical Investigation and Experimental Validation of a New Recuperator Design for Aero Engines Applications

2017 ◽  
Author(s):  
Zinon Vlahostergios ◽  
Dimitrios Misirlis ◽  
Michael Flouros ◽  
Christina Salpingidou ◽  
Stefan Donnerhack ◽  
...  
Keyword(s):  
Fuel Consumption ◽  
Waste Heat ◽  
External Pressure ◽  
Pollutant Emissions ◽  
Pressure Losses ◽  
Low Pressure Turbine ◽  
Heat Exchanger Design ◽  
Aero Engine ◽  
Pollutants Emission ◽  
Aero Engines

Targeting the development of more efficient aero engine designs, various concepts have been considered through the previous years, among which is the Intercooled Recuperative Aero engine (IRA) concept. In the IRA concept a system of heat exchangers is mounted in the hot-gas exhaust nozzle, downstream of the low-pressure turbine focusing on the exploitation of the waste heat exhaust gasses for preheating the compressor discharge air just before the latter enters the combustion chamber, resulting in fuel consumption and pollutants emission reduction. In the present work a new heat exchanger design for use as a recuperator is proposed for possible implementation in the IRA engine, based on an annular configuration design which is more easily integrated in an aero engine. The new recuperator external pressure losses are computationally and experimentally investigated for laboratory conditions, providing very good agreement. Additionally, the pressure losses just before the recuperator were further minimized by introducing riblet films inside the exhaust conical nozzle. The optimized recuperator characteristics were included in a thermodynamic analysis of the IRA engine and it was shown that considerable improvement in fuel consumption and pollutant emissions reduction could be achieved.

Cost Effectiveness Optimization of Component Improvements of a Turbofan Engine Using Genetic Algorithm

2015 ◽  
Author(s):  
Jason Yobby ◽  
Daniel S. Raja ◽  
Terry X. Yan
Keyword(s):  
Genetic Algorithm ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Pressure Ratio ◽  
Specific Fuel Consumption ◽  
Performance Criteria ◽  
Nozzle Pressure Ratio ◽  
Exit Nozzle ◽  
Nozzle Pressure ◽  
Specific Thrust

In this paper, we examined an imaginary underperforming prototype of a real high bypass-ratio turbofan gas turbine engine that has been assembled to specifications. The prototype was designed and assembled to generate a predetermined value of specific thrust while consuming fuel at a predefined specific fuel consumption value. To meet the required performance targets, improvements needed to be made to one or more of the engine components. In most real world scenarios, the improvement of any or all engine parameters pertaining to its performance is tied to a cost per percentages of improvements of individual component in the engine. There is always a narrow room for improvement in each or all of the components. However, the improvements come with high costs, since the engine has been designed in an efficient way to begin with. The cost of improvement of each component is indexed by a dollar cost per percent value of the component performance characteristics. It is of technical and economic importance to find a combination of performance improvements of each of the components that yields the lowest overall rework cost, thereby the total design cost, given the specified engine performance criteria. To achieve this goal, simulations for a real gas turbine turbofan cycle are performed in conjunction with the genetic algorithm (GA). A single objective (i.e. total improvement cost) GA with two constraints (i.e. desired values of specific thrust and specific fuel consumption) and eight degrees of freedom (i.e. diffuser pressure ratio, fan polytropic efficiency, compressor polytropic efficiency, burner efficiency, burner pressure drop ratio, turbine polytropic efficiency, fan duct exit nozzle pressure ratio, core duct exit nozzle pressure ratio) is employed. As a result, we have found the lowest overall cost associated with the improvements for each of the components.

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