Performance of Axial-Flow Turbines

1948 ◽  
Vol 159 (1) ◽  
pp. 230-244 ◽  
Author(s):  
D. G. Ainley
Keyword(s):  
Gas Turbine ◽  
Experimental Work ◽  
Gas Flow ◽  
High Efficiency ◽  
Gas Turbine Engine ◽  
Steam Turbines ◽  
Aerodynamic Design ◽  
Turbine Engine ◽  
Turbine Performance ◽  
Economic Operation

The advent of the gas-turbine engine, with its absolute dependence on high component efficiencies for reasonable economic operation, and the necessity for new materials which will withstand high stresses at much greater temperatures than encountered on steam turbines, has led engineers to review the design of turbines closely both from an aerodynamic and a mechanical standpoint: there is still a great deal to be learnt. Reeman† has outlined the present mathematical approach to the design of turbines and surveyed very comprehensively the mechanical problems that are involved. This paper is intended to indicate the manner in which the aerodynamic design of a turbine has developed from that of its steam predecessor and, in particular, surveys some recent experimental work relating to turbine performance. The general aims of the experimental work are to explore the gas-flow processes within a turbine stage, to determine the associate aerodynamic efficiencies, and to gain some understanding of the limitations imposed upon the aerodynamic design of a stage by the necessity for the high efficiency which is required for economic operation of a gas-turbine engine. The data that have so far come to light, though incomplete, illustrate the general overall characteristics of high- and low-reaction turbines, and also the effect that high Mach number or low Reynolds number may have on turbine performance. To conclude the paper, a brief description of the technique adopted for adequate full-scale testing of turbines is presented. This covers the essential points of, power absorption, instrumentation, and safety precaution. The effects of errors in measurements are also discussed.

scholarly journals Comparison of Coriolis and Turbine Type Flow Meters for Fuel Measurement in Gas Turbine Testing

1993 ◽  
Author(s):  
J. D. MacLeod ◽  
W. Grabe
Keyword(s):  
Steady State ◽  
Gas Turbine ◽  
Mass Flow ◽  
Gas Turbines ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Turbine Flowmeter ◽  
Turbine Performance ◽  
Coriolis Flowmeter ◽  
Project Objectives

The Machinery and Engine Technology (MET) Program of the National Research Council of Canada (NRCC) has established a program for the evaluation of sensors to measure gas turbine engine performance accurately. The precise measurement of fuel flow is an essential part of steady-state gas turbine performance assessment. Prompted by an international engine testing and information exchange program, and a mandate to improve all aspects of gas turbine performance evaluation, the MET Laboratory has critically examined two types of fuel flowmeters, Coriolis and turbine. The two flowmeter types are different in that the Coriolis flowmeter measures mass flow directly, while the turbine flowmeter measures volumetric flow, which must be converted to mass flow for conventional performance analysis. The direct measurement of mass flow, using a Coriolis flowmeter, has many advantages in field testing of gas turbines, because it reduces the risk of errors resulting from the conversion process. Turbine flowmeters, on the other hand, have been regarded as an industry standard because they are compact, rugged, reliable, and relatively inexpensive. This paper describes the project objectives, the experimental installation, and the results of the comparison of the Coriolis and turbine type flowmeters in steady-state performance testing. Discussed are variations between the two types of flowmeters due to fuel characteristics, fuel handling equipment, acoustic and vibration interference and installation effects. Also included in this paper are estimations of measurement uncertainties for both types of flowmeters. Results indicate that the agreement between Coriolis and turbine type flowmeters is good over the entire steady-state operating range of a typical gas turbine engine. In some cases the repeatability of the Coriolis flowmeter is better than the manufacturers specification. Even a significant variation in fuel density (10%), and viscosity (300%), did not appear to compromise the ability of the Coriolis flowmeter to match the performance of the turbine flowmeter.

Training Future Gas Turbine Performance Engineers

2007 ◽  
Author(s):  
V. Pachidis ◽  
P. Pilidis ◽  
I. Li
Keyword(s):  
Gas Turbine ◽  
Thermal Power ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Performance Simulation ◽  
Turbine Engine ◽  
Turbine Performance ◽  
Auxiliary Power ◽  
Engine Testing ◽  
The Uk

The performance analysis of modern gas turbine engine systems has led industry to the development of sophisticated gas turbine performance simulation tools and the utilization of skilled operators who must possess the ability to balance environmental, performance and economic requirements. Academic institutions, in their training of potential gas turbine performance engineers have to be able to meet these new challenges, at least at a postgraduate level. This paper describes in detail the “Gas Turbine Performance Simulation” module of the “Thermal Power” MSc course at Cranfield University in the UK, and particularly its practical content. This covers a laboratory test of a small Auxiliary Power Unit (APU) gas turbine engine, the simulation of the ‘clean’ engine performance using a sophisticated gas turbine performance simulation tool, as well as the simulation of the degraded performance of the engine. Through this exercise students are expected to gain a basic understanding of compressor and turbine operation, gain experience in gas turbine engine testing and test data collection and assessment, develop a clear, analytical approach to gas turbine performance simulation issues, improve their technical communication skills and finally gain experience in writing a proper technical report.

scholarly journals 2MW Class High Efficiency Gas Turbine IM270 for Co-Generation Plants

1996 ◽  
Author(s):  
Hideo Kobayashi ◽  
Shogo Tsugumi ◽  
Yoshio Yonezawa ◽  
Riuzou Imamura
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Mechanical Design ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Maintenance Cost ◽  
Turbine Engine ◽  
Generation Plant ◽  
Emission Regulation ◽  
Heavy Duty Gas Turbine

IHI is developing a new heavy duty gas turbine engine for 2MW class co-generation plants, which is called IM270. This engine is a simple cycle and single-spool gas turbine engine. Target thermal efficiency is the higher level in the same class engines. A dry low NOx combustion system has been developed to clear the strictest emission regulation in Japan. All parts of the IM270 are designed with long life for low maintenance cost. It is planned that the IM270 will be applied to a dual fluid system, emergency generation plant, machine drive engine and so on, as shown in Fig.1. The development program of IM270 for the co-generation plant is progress. The first prototype engine test has been started. It has been confirmed that the mechanical design and the dry low NOx system are practical. The component tuning test is being executed. On the other hand, the component test is concurrently in progress. The first production engine is being manufactured to execute the endurance test using a co-generation plant at the IHI Kure factory. This paper provides the conceptual design and status of the IM270 basic engine development program.

scholarly journals A Model and State-Space Controllers for an Intercooled, Regenerated (ICR) Gas Turbine Engine

1992 ◽  
Author(s):  
J. W. Watts ◽  
T. E. Dwan ◽  
R. W. Garman
Keyword(s):  
State Space ◽  
Gas Turbine ◽  
High Efficiency ◽  
Linear Quadratic Regulator ◽  
Gas Turbine Engine ◽  
Linear Quadratic ◽  
Turbine Engine ◽  
Simulation Language ◽  
Linear State ◽  
High Level

A two-and-one-half spool gas turbine engine was modeled using the Advanced Computer Simulation Language (ACSL), a high level simulation environment based on FORTRAN. A possible future high efficiency engine for powering naval ships is an intercooled, regenerated (ICR) gas turbine engine and these features were incorporated into the model. Utilizing sophisticated instructions available in ACSL linear state-space models for this engine were obtained. A high level engineering computational language, MATLAB, was employed to exercise these models to obtain optimal feedback controllers characterized by the following methods: (1) state feedback; (2) linear quadratic regulator (LQR) theory; and (3) polygonal search. The methods were compared by examining the transient curves for a fixed off-load, and on-load profile.

scholarly journals Turbine Rebuild Effects on Gas Turbine Performance

1992 ◽  
Author(s):  
J. D. MacLeod ◽  
B. Drbanski
Keyword(s):  
Gas Turbine ◽  
National Research Council ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
New Methods ◽  
Turbine Performance ◽  
Turboprop Engine ◽  
Project Objectives ◽  
Performance Variations

The Engine Laboratory of the National Research Council of Canada (NRCC), with the assistance of Standard Aero Ltd., has established a program for the evaluation of component deterioration on gas turbine engine performance. As part of this project, a study of the effects of turbine rebuild tolerances on overall engine performance was undertaken. This study investigated the range of performance changes that might be expected for simply disassembling and reassembling the turbine module of a gas turbine engine, and how these changes would influence the results of the component fault implantation program. To evaluate the effects of rebuilding the turbine on the performance of a single spool engine, such as Allison T56 turboprop engine, a series of three rebuilds were carried out. This study was performed in a similar way to a previous NRCC study on the effects of compressor rebuilding. While the compressor rebuild study had found performance changes in the order of 1% on various engine parameters, the effects of rebuilding the turbine have proven to be even more significant. Based on the results of the turbine rebuild study, new methods to improve the assurance of the best possible tolerances during the rebuild process are currently being addressed. This paper describes the project objectives, the experimental installation, and the results of the performance evaluations. Discussed are performance variations due to turbine rebuilds on engine performance characteristics. As the performance changes were significant, a rigorous measurement uncertainty analysis is included.

Development of the Centaur Type H Gas Turbine Engine

1985 ◽  
Author(s):  
G. L. Padgett ◽  
W. W. Davis
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
State Of The Art ◽  
Gas Turbine Engine ◽  
Development Plan ◽  
Inlet Temperature ◽  
Market Place ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Computer Aided

In response to the needs of the market place for turbines in the 5000 to 6000 hp class, Solar Turbines Incorporated has responded with an uprate of their Centaur engine. Discussed in this paper are the features of the uprated engine, the Development Plan and the methodology for incorporating into the design the advanced aerodynamic and mechanical technology of the Mars engine. The Mars engine is a high efficiency 12,500 hp engine which operates at a turbine inlet temperature of 1935°F. State-of-the-art computer aided methods have been applied to produce the design, and the results from this approach are displayed.

Improving the performance of gas turbine engine blades based on functionally oriented coatings

2021 ◽  
pp. 435-441
Author(s):  
A.N. Mikhaylov ◽  
D.A. Mikhaylov ◽  
E.A. Sheiko ◽  
A.A. Colodyazhny
Keyword(s):  
Mathematical Models ◽  
Titanium Alloys ◽  
Gas Turbine ◽  
Surface Hardening ◽  
Gas Turbine Engine ◽  
Electrospark Alloying ◽  
Steam Turbines ◽  
Turbine Engine ◽  
Technological Processes

Mathematical models have been developed for the surface hardening of VT20 and OT4 titanium alloys by electrospark alloying, which can be used in the design of technological processes for the manufacture of titanium blades of steam turbines.

Rational Design of Gas Turbine Engine Compressor to Provide the Required Dynamic Strength Level of Rotor Blades

2016 ◽  
Author(s):  
Daria Kolmakova ◽  
Grigorii Popov ◽  
Aleksandr Shklovets ◽  
Aleksandr Ermakov
Keyword(s):  
Gas Turbine ◽  
Rational Design ◽  
Gas Flow ◽  
Dynamic Strength ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Dynamic Stresses ◽  
Turbine Engine ◽  
Acceptable Method ◽  
Flow Oscillations

Compressors of gas turbine engines often operate under the conditions of uneven gas flow. Oscillations of the blades occur under the influence of circumferential flow unevenness. The goal of the research was to find an acceptable method of reducing the level of dynamic stresses in the rotor blades. Motivation for the study was the problem of destruction of rotor blades of the last stage of Intermediate Pressure Compressor (IPC) which has been designed and produced at JSC “Kuznetsov” (Russia). The source of circumferential flow unevenness was middle annular frame located downstream the IPC. Seven struts with different maximum thickness are arranged irregularly in support passage. The first approaches propose to reduce the dynamic stresses in blades by detuning the blades from the dangerous harmonic due to changes in their natural frequency. The next two consist in reducing the circumferential unevenness of flow. Thus, this study gives the ideas about methods of improving the dynamic strength of rotor blades of gas turbine engine compressors. On the basis of existing conditions (under development or existing compressor) it allows the selection of the most suitable method for reducing dynamic stresses.

scholarly journals Theory of gas turbine engine optimal gas generator

2019 ◽  
Vol 18 (2) ◽  
pp. 52-61
Author(s):  
A. V. Grigoriev ◽  
A. A. Kosmatov ◽  
О. A. Rudakov ◽  
A. V. Solovieva
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Flow ◽  
Turbine Blades ◽  
Target Function ◽  
Gas Turbine Engine ◽  
Gas Generator ◽  
Joint Operation ◽  
Turbine Engine ◽  
Wide Range

The article substantiates the necessity of designing an optimal gas generator of a gas turbine engine. The generator is to provide coordinated joint operation of its units: compressor, combustion chamber and compressor turbine with the purpose of reducing the period of development of new products, improving their fuel efficiency, providing operability of the blades of a high-temperature cooled compressor turbine and meeting all operational requirements related to the operation of the optimal combustion chamber including a wide range of stable combustion modes, high-altitude start at subzero air and fuel temperature conditions and prevention of the atmosphere pollution by toxic emissions. Methods of optimizing the parameters of coordinated joint operation of gas generator units are developed. These parameters include superficial flow velocities in the boundary interface cross sections between the compressor and the combustion chamber, as well as between the combustion chamber and the compressor turbine. The effective efficiency of the engine thermodynamic cycle is the optimization target function. The required depth of the turbine blades cooling is a functional constraint evaluated with account for calculations of irregularity and instability of the gas temperature field and the actual flow turbulence intensity at the blades’ inlet. We carried out theoretical analysis of the influence of various factors on the gas flow that causes changes in the flow total pressure in the channels of the gas generator gas dynamic model, i.e. changes in the efficiencies of its units. It is shown that the long period (about five years) of the engine final development time, is due to the necessity to perform expensive full-scale tests of prototypes, in particular, it is connected with an incoordinate assignment in designing the values of the flow superficial velocities in the boundary sections between the gas generator units. Designing of an optimal gas generator is only possible on the basis of an integral mathematical model of an optimal combustion chamber.

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