Investigation of Transient Performance of an Auxiliary Power Unit Microturbine Engine

2006 ◽  
Author(s):  
SooYong Kim ◽  
JunYoung Park ◽  
Victor L. Goldenberg
Keyword(s):  
Control System ◽  
Power Unit ◽  
Transient Process ◽  
Pressure Ratio ◽  
Load Condition ◽  
Design Stage ◽  
Turbine Engine ◽  
Auxiliary Power Unit ◽  
Air Volume ◽  
Auxiliary Power

Prevention of compressor surge is one of the most important tasks in operation of gas turbine engine. The easiest way to see the phenomena is to show the static and dynamic operation characteristic on the map. Its operation zone will be restricted by the surge limit and, static and transient process must have some margin for it. Surge margin of a static regime is normally chosen during its design stage. Safe operation during part load condition without facing the surge is an indispensable task for control system design and a swift response from the engine is required to avoid it. Effect of rotor moment of inertia, air/gas volumes and heat transfer are factors to cause the transition from the static line. In case a large volume such as heat exchanger exists in the system it will exert a substantial influence to dynamic characteristics. In the present paper, influence of air volume bled from the compressor exit on transient process is investigated with an example of an auxiliary power unit micro-turbine engine. A typical compressor characteristic with scaling was used for the calculation. Turbine mass, pressure ratio, rotation speed, power and moment are calculated based on mass and work conservation. Result from the present study can give a guidance to design the control system. A computer program is developed to calculate the dynamic process using the MathCAD commercial software. Air volume is changed from 0.02 to 6 m3.

scholarly journals Design and Test Evaluation of Full Authority Digital Electronic Control System for an Auxiliary Power Unit

2018 ◽  
Vol 36 (6) ◽  
pp. 1102-1107
Author(s):  
Kai Peng ◽  
Fan Yang ◽  
Ding Fan ◽  
Linfeng Gou ◽  
Hongliang Xiao ◽  
...  
Keyword(s):  
Control System ◽  
Power Unit ◽  
Digital Control ◽  
Electronic Control ◽  
Digital Control System ◽  
Control Laws ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Electronic Control System ◽  
Key Techniques

A helicopter auxiliary power unit (APU) is initially equipped with a hydro-mechanical control system (HMC). Because HMC's complex structure is difficult to be modified to realize sophisticated control algorithms and the APU is faced with the need for performance improvement, it is urgently necessary to carry out digital control modification of HMC. Based on the analysis of control laws of the original HMC and differences between HMC and digital control system, key techniques involved in the digital control system are studied, such as overall structure, control laws and fuel system based on electric fuel pump, and finally a full authority digital electronic control system (FADEC) is developed for APU. Functions, performances and key techniques of the FADEC system are evaluated on test rig, and the test results show functions of original control system are enhanced and performances of APU are improved more effectively under the control of the designed FADEC compared with the original HMC.

scholarly journals Method of coordinating air starter and auxiliary power unit joint operation

2020 ◽  
pp. 5-13
Author(s):  
Grigory Popov ◽  
◽  
Vasily Zubanov ◽  
Valeriy Matveev ◽  
Oleg Baturin ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Gas Turbine Engine ◽  
Working Process ◽  
Joint Operation ◽  
Turbine Engine ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Start Up ◽  
Air Turbine

The presented work provides a detailed description of the method developed by the authors for coordinating the working process of the main elements of the starting system for a modern gas turbine engine for a civil aviation aircraft: an auxiliary power unit (APU) and an air turbine – starter. This technique was developed in the course of solving the practical problem of selecting the existing APU and air turbine for a newly created engine. The need to develop this method is due to the lack of recommendations on the coordination of the elements of the starting system in the available literature. The method is based on combining the characteristics of the APU and the turbine, reduced to a single coordinate system. The intersection of the characteristic’s lines corresponding to the same conditions indicates the possibility of joint operation of the specified elements. The lack of intersection indicates the impossibility of joint functioning. The calculation also takes into account losses in the air supply lines to the turbine. The use of the developed method makes it possible to assess the possibility of joint operation of the APU and the air turbine in any operating mode. In addition to checking the possibility of functioning, as a result of the calculation, specific parameters of the working process at the operating point are determined, which are then used as initial data in calculating the elements of the starting system, for example, determining the parameters of the turbine, which in turn allow providing initial information for calculating the starting time or the possibility of functioning of the starting system GTE according to strength and other criteria. The algorithm for calculating the start-up time of the gas turbine engine was also developed by the authors and implemented in the form of an original computer program. Keywords: gas turbine engine start-up, GTE starting system, air turbine, methodology, joint work, auxiliary power unit, power, start-up time, characteristics matching, coordination, operational characteristics, computer program.

scholarly journals Gemini T-20G-8 XM1 Tank APU

1981 ◽  
Author(s):  
C. Rodgers ◽  
J. Zeno ◽  
E. A. Drury ◽  
A. Karchon
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Weather Conditions ◽  
Cold Weather ◽  
Turbine Engine ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Generator Sets ◽  
Main Engine ◽  
The U.S

Auxiliary power is often provided on combat vehicles in the U.S. Army for battery charging, operation of auxiliary vehicle equipment when the main engine is not running, or to provide assistance in starting the main engine in extreme cold weather conditions. The use of a gas turbine for these applications is particularly attractive, due to its small size and lightweight. In November 1978, the U.S. Army Tank-Automotive Research and Development Command, Warren, MI awarded a contract to the Turbomach Division of Solar Turbines International, San Diego, CA, for the development of a 10 kW 28 vdc gas turbine powered auxiliary power unit (APU) for installation in the XM1 main battle tank. This paper describes the general features of the Solar Turbomach T-20G-8 Auxiliary Power Unit, a single-shaft gas turbine driven generator set which has been developed under this contract. This APU is one of the family of Gemini powered APUs and is a derivative of the U.S. Army 10 kW gas turbine engine-driven, 60 and 400 Hz generator sets developed by Solar. The electrical components were newly developed for this particular application. Currently, the APU is in qualification testing both in the laboratory and in the XM1 main battle tank.

Analysis of Gas Turbine Engines Auxiliary Power Units

2014 ◽  
Vol 533 ◽  
pp. 13-16
Author(s):  
Yu Yu Zuo
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Ground Support ◽  
Auxiliary Power Unit ◽  
Aircraft Systems ◽  
Auxiliary Power ◽  
Auxiliary Power Units

As aircraft became more complex a need was created for a power source to operate the aircraft systems on the ground without the necessity for operating the aircrafts main engines. This became the task of the Auxiliary Power Unit (APU). The use of an APU on an aircraft also meant that the aircraft was not dependant on ground support equipment at an airfield. It can provide the necessary power for operation of the aircrafts Electrical, Hydraulic and Pneumatic systems. It should come as no surprise that the power unit selected to do this task is a Gas Turbine Engine.

A New System of Failure Warning and Monitoring Control System for Gas Turbine Compressor (GTC)/Auxiliary Power Unit (APU) of Aircrafts and a Sample Study

2012 ◽  
Vol 503-504 ◽  
pp. 1633-1638 ◽  
Author(s):  
Melih Cemal Kushan ◽  
Zhong Xiao Peng ◽  
Shu Zhi Peng
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Power Unit ◽  
Aviation Industry ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Gas Turbine Compressor ◽  
New System

One of the key elements of servicing the aviation industry is the provision and maintenance of first class equipment. In order to ensure a secure and effective flight of aircrafts in aviation, the ground supporting equipment which enables the planes to get off the ground without delaying the flight plans, has to be kept ready at all times [1].

scholarly journals The GTCP36-300, a Gas Turbine Auxiliary Power Unit for Advanced Technology Transport Aircraft

1986 ◽  
Author(s):  
L. M. Stohlgren ◽  
Lutz D. Werner
Keyword(s):  
Power Unit ◽  
State Of The Art ◽  
Pressure Ratio ◽  
Single Stage ◽  
Advanced Technology ◽  
Transport Aircraft ◽  
Auxiliary Power Unit ◽  
Cost Of Ownership ◽  
Auxiliary Power ◽  
Electrical Generator

The Garrett GTCP36-300 Series Auxiliary Power Unit is being developed for use on advanced technology transport aircraft in the 150-passenger size class. The first application will be the Airbus Industries A320 Aircraft. The APU uses a 6:1 pressure ratio, single-stage compressor and turbine, driving a single-stage load compressor and accessory gearbox. The 480 horsepower APU delivers compressed air to the aircraft pneumatic system and drives a customer furnished 90 kva, 24,000 rpm electrical generator. State-of-the-art aerodynamics, materials, and digital electronics are used to give the user-airlines an APU delivering maximum performance with minimum envelope, weight, and cost of ownership.

Modeling and Simulation of the Auxiliary Power System in Extended Range Electric Vehicle

2013 ◽  
Vol 397-400 ◽  
pp. 1858-1862 ◽  
Author(s):  
Ling Shan Chen ◽  
Xiao Le Wang ◽  
Xiang Er Huang ◽  
Pin Gan ◽  
Wei Cheng
Keyword(s):  
Control System ◽  
Electric Vehicle ◽  
Power Unit ◽  
Engine Speed ◽  
Torque Control ◽  
Decoupling Control ◽  
Vehicle Simulation ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Extended Range

To study the performance of auxiliary power unit in extended range electric vehicle, simulation model of auxiliary power unit and its control system are established with MATLAB/Simulink. The method of decoupling control achieved engine speed control and generator torque control. Finally actual power responds change of required power quickly.

scholarly journals Research on the Design Method of the Starting Process of Main Fuel Control system for Aviation Auxiliary Power Unit

2018 ◽  
Vol 227 ◽  
pp. 01004
Author(s):  
Yanan Guo ◽  
Ding Fan ◽  
Kai Peng ◽  
Fang Tian
Keyword(s):  
Control System ◽  
Power Unit ◽  
Design Method ◽  
System Control ◽  
Future Design ◽  
Auxiliary Power Unit ◽  
Fuel Flow ◽  
Auxiliary Power ◽  
Starting Process ◽  
And Control

This paper analyzed the main fuel control system of the auxiliary power unit (APU), explored the starting process of the main fuel flow control system control law and control algorithm. Focus on analyzing the interpolation table that is involved in the controller of the starting process, restoring its physical meaning. The design method of the main fuel flow controller for the starting process of the APU is summarized. It’s a valuable reference for the future design of the control system of both aero-engine and auxiliary power unit.

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