Performance Analysis of Jet Engine of Aircraft

The jet engine family includes the rocket jet, pulse jet, ram jet & gas turbine powered jet. The gas turbine powered jet is further broken down into the turbo jet, turbo propeller, and turbo shaft & turbofans types. These four types of engines are the most commonly used in today’s aircraft. Kiran aircraft is the basic jet trainer used in Indian air force. Kiran MkII is fitted with Orpheus engine. The engine is a straight flow turbo jet type fitted with a seven stage axial flow compressor and develops 4200+- 84 lbs/ 1909+- 38 kg static thrust at 9500 rpm at sea level. This increase to a maximum at 10,000 ft, due to the characteristics of high pressure fuel pumps in the engine fuel system. Above this height the thrust developed reduces as altitude increases. Air at atmospheric pressure is compressed adiabatically, during its passage across the compressor and diffuser, to approx 4 atm. The pressure and temperature increases and volume decreases at this stage. In the combustion chamber it is supplied at constant pressure thereby considerably increasing the volume of the air. Then during passage of the gas stream through the rear end of the combustion chamber, stationary vanes, turbine and exhaust cone, there is adiabatic expansion which is completed in the propelling nozzle with increased volume and decreased pressure at the end of the propelling nozzle, there is rejection of heat at constant pressure. The Orpheus engine which is fitted in Kiran MkII jet aircraft is performing an excellent job as it is used for giving the training to the fighter pilots.

Thermodynamic Design of a Small-Scale Gas Turbine Engine Family

The paper presents a procedure for selecting work cycle parameters and describes thermodynamic design of a small-scale gas turbine engine family consisting of a small-scale gas turbine engine and a gas turbine plant comprising a free turbine driving a power generator, on the basis of a standardized gas generator. In order to select reasonable work cycle parameter values for the small-scale gas turbine engine and gas turbine plant we used a non-linear optimisation technique accounting for functional and parametric constraints as implemented in the ASTRA CAE software. Calculation results allowed us to plot the locally optimal work cycle parameter regions for the small-scale gas turbine engine and gas turbine plant according to the efficiency criteria for both engines, which are specific fuel consumption and net energy conversion efficiency. Taking the constraints into account, we selected reasonable values for the standardized gas generator parameters within the compromise region obtained, specifically the turbine inlet temperature and compressor pressure ratio. Our quantitative results show how the efficiency indices decline in the engine family featuring a standardized gas generator as compared to engines equipped with individually tailored gas generators. Designing a standardized gas generator in advance makes it possible to decrease engine development costs and time, ensure a higher reliability and a lower cost of production.

Modular 9.0L and 4.5L Non-Road Spark-Ignited Engines for Power Generation

Following the successful commercial use of a 9.0L, V-8 automotive-derivative engine for stationary power generation, a new 4.5L, four-cylinder engine has been developed utilizing a modular family design approach. Substantial commonality of power cylinder components has been achieved including the complete power cylinder and cylinder head. This paper describes the design and development approach to the engine family. These spark-ignited engines are typically used for standby emergency power and demand response applications utilizing commercial grade natural gas or propane. Driving a synchronous electrical generator operating at 60 HZ or 50Hz, engine speeds are either 1800 rpm/3600 rpm or 1500 rpm/3000 rpm respectively, depending upon selection of either a 2-pole or 4-pole alternating current generator. Designed for stoichiometric combustion, the engine configurations can include naturally-aspirated, turbocharged or turbocharged and after-cooled versions. Depending upon end-use applications, exhaust emissions technology and regulatory compliance can be met solely through engine calibration or inclusion of a 3-way catalyst with active air-fuel ratio control. Since the 9.0L engine version was successfully introduced in 2012, significant efforts have been undertaken to achieve commonality of desired features between the existing veeengine and the future in-line versions, including optimization of performance characteristics in consideration of future power rating structures. Starting from 9.0L commercial introduction, the content herein specifically describes the development of the new 4.5L engine with regard to design and analysis.

Thermodynamic designing of the small-scale gas turbine engine family with common core

The paper describes the method of selecting the working process parameters of a family of small-scale gas turbine engines (GTE) with common core. As an example, the thermodynamic design of a family of small-scale gas turbine engines (SGTE) with common core was carried out. The engine family includes a small-scale turbojet engine (STJE) and a gas turbine plant (GTP), which electric generator is driven by power turbine. The selection of rational values for the working process parameters of STJE and GTP was carried out in CAE system ASTRA on the basis of nonlinear optimization of these parameters, taking into account functional and parametric constraints. The quantitative results of deterioration in the performance of the engines of the family with common core are obtained in comparison with the engines with the optimum core for each type. However, the advanced creation of a common core can reduce the cost and timing of the engine creation, ensure its higher reliability (due to the development of the base common core) and reduce the cost of its production. The method of selecting the parameters of the working process of the GTE family with common core presents the solution to more complex problems, such as the possibility of developing a family consisting of five engines: a turbojet engine, turbofan engine, turbofan engine with a complex cycle, GTE with power turbine (GTE-PT), GTE-PT with recovery.