Moisture Condensation Effect on Turbine Performance Tests

2004 ◽  
Author(s):  
I. Roumeliotis ◽  
K. Mathioudakis
Keyword(s):  
Turbine Engines ◽  
Performance Tests ◽  
Gas Turbine Engines ◽  
Performance Parameters ◽  
Atmospheric Air ◽  
Turbine Performance ◽  
Working Medium ◽  
Component Test ◽  
Moisture Condensation ◽  
Condensation Effect

Water is always present in the atmospheric air in the form of vapour, affecting the operation of turbomachinery components in gas turbine engines. Due to water presence in the working medium, condensation may occur, which can influence the thermal performance of the component and alter the measurements taken for calculations. This can lead to erroneous evaluation of component performance parameters during development performance tests. Procedures to detect condensation and if possible to correct the measurements during engine or component test should be used to avoid such situations. A method allowing the prediction of condensation and the correction of the measurements for low speed expansion is presented. The method is implemented in turbine testing measurements where condensation occurs and the results show that condensation may be predicted and its effects corrected.

scholarly journals Some Aerodynamic Problems of Aircraft Engines: Fifty Years After -The 2007 IGTI Scholar Lecture-

2009 ◽  
Vol 131 (3) ◽  
Author(s):  
Edward M. Greitzer
Keyword(s):  
Gas Turbine ◽  
Collaborative Research ◽  
Research Process ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Jet Engines ◽  
Organizational Boundaries ◽  
Turbine Performance ◽  
Single Discipline

Problems of high technological interest, for example the development of gas turbine engines, span disciplinary, and often organizational, boundaries. Although collaboration is critical in advancing the technology, it has been less a factor in gas turbine research. In this paper it is proposed that step changes in gas turbine performance can emerge from collaborative research endeavors that involve the development of integrated teams with the needed range of skills. Such teams are an important aspect in product development, but they are less familiar and less subscribed to in the research community. The case histories of two projects are given to illustrate the point: the development of the concept of “smart jet engines” and the Silent Aircraft Initiative. In addition to providing a capability to attack multidisciplinary problems, the way in which collaboration can enhance the research process within a single discipline is also discussed.

Some Aerodynamic Problems of Aircraft Engines: Fifty Years After

2007 ◽  
Author(s):  
Edward M. Greitzer
Keyword(s):  
Gas Turbine ◽  
Research Process ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Jet Engines ◽  
Case Histories ◽  
Disciplinary Boundaries ◽  
Turbine Performance ◽  
Single Discipline

Problems of high technological interest, for example the development of gas turbine engines, span disciplinary boundaries. Collaboration is critical in advancing the technology, but it has been less a factor in gas turbine research. In this paper it is proposed that step changes in gas turbine performance can emerge from such collaborative endeavors. In these, success depends on the development of integrated teams with the appropriate range of skills. This is well known in product development, but it is less familiar, and less subscribed to, in the research community. Case histories of two projects are given to illustrate the point: the development of the concept of “smart jet engines” and the Silent Aircraft Initiative. In addition to providing the ability to attack multidisciplinary issues discussion is also given about the way in which collaboration can enhance the research process within a single discipline.

Directions in High Temperature Intermetallics Research

1988 ◽  
Vol 133 ◽  
Author(s):  
Dennis M. Dimiduk ◽  
Daniel B. Miracle
Keyword(s):  
High Temperature ◽  
Air Force ◽  
Evolutionary Process ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Paper Briefly ◽  
Research Directions ◽  
Intermetallic Materials ◽  
Turbine Performance ◽  
Structural Intermetallic

ABSTRACTStructural intermetallic materials have undergone an evolutionary process whereby some of the materials could provide major payoffs in gas turbine engines. This maturation of select intermetallic systems has provided significant hope for making still greater advances in turbine performance through further developments in other intermetallic materials. The same maturation process has highlighted specific limitations and requirements which are key to the utilization of intermetallic systems. This paper briefly reviews some critical ground rules for high temperature intermetallics development and identifies research directions being pursued by the Air Force for advancing intermetallic materials.

Lost Thrust Methodology for Gas Turbine Engine Performance Analysis

2005 ◽  
Author(s):  
B. Roth ◽  
J. de Luis
Keyword(s):  
Performance Analysis ◽  
Gas Turbine ◽  
Engine Performance ◽  
Separate Flow ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
The Real ◽  
Turbine Performance ◽  
Definition Of

This paper presents and evaluates a lost thrust method for analysis of thermodynamic performance in gas turbine engines. This method is based on the definition of a hypothetical ideal engine that is used as a point of comparison to evaluate performance of the real engine. Specifically, component loss is quantified in terms of decrements in thrust of the real engine relative to the ideal engine having the same design point cycle. These lost thrust decrements provide a basis for accurately evaluating the performance cost of component losses while simultaneously accounting for all component interactions. The analysis algorithm is formally developed in detail and is then demonstrated for a typical separate flow turbofan engine. Various scenarios are examined and the results of these exercises are used to draw conclusions regarding the strengths and weaknesses of this approach to gas turbine performance analysis.

Development of a Novel Technique to Address Compressor Fouling in a Turbo-Shaft Engine

2013 ◽  
Author(s):  
S. Saji Kumar ◽  
S. Esakki Muthu ◽  
S. Dileep ◽  
R. K. Mishra
Keyword(s):  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Performance Parameters ◽  
Gas Generator ◽  
Time Intervals ◽  
Optimum Time ◽  
Power Turbine ◽  
Washing Process ◽  
Base Platform ◽  
Engine Power

Compressor washing is commonly used in gas turbine engines to retrieve engine power. Severity of fouling should be known to decide on mounted or uninstalled washing and also to optimize the time and money. The present study aims to develop a system for predicting and scheduling the washing process. One 1 MW turbo shaft engine has been taken as the model for this study. The deviations in performance parameters have been quantified based on test data over a period. Deterioration of engine health parameters namely efficiency and flow capability of compressor, gas generator turbine and power turbine are considered for analysis. Sensitivity analysis and ranking of the measurements were done using a correlative technique suggested by Stamatis. The interdependency and observability of the measurements were checked. The fault signatures of selected measurement set on component degradations were isolated and estimation charts were formed to predict the optimum time intervals for compressor washing. The study forms a base platform to apply techniques like artificial neural networks for the accurate forecasting of optimum cleaning intervals for turbo shaft engines.

Parametric Analysis of Existing Gas Turbines With Inlet Evaporative and Overspray Fogging

2002 ◽  
Author(s):  
R. Bhargava ◽  
C. B. Meher-Homji
Keyword(s):  
Gas Turbine ◽  
Performance Improvement ◽  
Gas Turbines ◽  
Parametric Analysis ◽  
Design Parameters ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Performance Parameters ◽  
Wide Range ◽  
Turbine Design

With deregulation in the power generation market and the need for flexibility in terms of power augmentation during periods of high electricity demand, power plant operators all over the world are exploring means to augment power from both existing and new gas turbines. An approach becoming increasingly popular is that of high pressure fogging. In this paper, the results of a comprehensive parametric analysis on the effects of inlet fogging on a wide range of existing gas turbines have been presented. Both evaporative and overspray fogging conditions have been analyzed. The results of this study show that the performance parameters indicative of inlet fogging effects have definitive correlation with the key gas turbine design parameters. In addition, this study indicates that aeroderivative gas turbines, in comparison to the industrial machines, have higher performance improvement due to the inlet fogging effects. Plausible reasons for the observed trends are discussed in this paper. This paper represents the first systematic study on the effects of inlet fogging for a large number (a total of 67) of gas turbine engines available from major gas turbine manufacturers.

A New Method of Predicting the Performance of Gas Turbine Engines

1991 ◽  
Vol 113 (1) ◽  
pp. 106-111 ◽  
Author(s):  
Wang Yonghong
Keyword(s):  
Gas Turbine ◽  
New Method ◽  
Turbine Engines ◽  
Computation Method ◽  
Gas Turbine Engines ◽  
Inverse Algorithm ◽  
New Model ◽  
Turbine Performance ◽  
Stable Performance ◽  
The Common

This paper points out that the turbine performance computation method used widely at present in solving the performance of gas turbine engines is a numerically unstable algorithm. Therefore a new method, namely an inverse algorithm, is proposed. This paper then further proposes a new mathematical model for solving the stable performance of gas turbine engines. It has the features of not only being suitable for an inverse algorithm for turbine performance, but also having fewer dimensions than existing models. It has the advantages of high accuracy, rapid convergence, good stability, fewer computations, and so forth. It has been fully proven that the accuracy of the new model is much greater than that of the common model for gas turbine engines. Additionally, the time consumed for solving the new model is approximately 1/4~1/10 of that for the common model. Therefore, it is valuable in practice.

scholarly journals A New Method of Predicting the Performance of Gas Turbine Engines

1990 ◽  
Author(s):  
Wang Yonghong
Keyword(s):  
Gas Turbine ◽  
New Method ◽  
Turbine Engines ◽  
Computation Method ◽  
Gas Turbine Engines ◽  
Inverse Algorithm ◽  
New Model ◽  
Turbine Performance ◽  
Stable Performance ◽  
The Common

This paper points out that the turbine performance computation method used widely at present in solving the performance of gas turbine engines is a numerically instable algorithm. So a new method, namely inverse algorithm, is proposed. This paper then further proposes a new mathematical model of solving the stable performance of gas turbine engines. It has the features of not only being suitable for inverse algorithm for turbine performance, but also having less dimensions than existing models. So it has the advantages of high accuracy, rapid convergence, good stability, less computations, and so forth. It has been fully proven that the accuracy of the new model is much greater than that of the common model for gas turbine engines. Additionally, the time consumed for solving the new model is approximately 1 / 4 ∼ 1 / 10 of that for the common model. Therefore, it is valuable in practice.

Gas Screen in Components of Gas Turbine Engines

1997 ◽  
Vol 28 (7-8) ◽  
pp. 536-542
Author(s):  
A. A. Khalatov ◽  
I. S. Varganov
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Screen
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