Compressor Coating Effects on Gas Turbine Engine Performance

1991 ◽  
Vol 113 (4) ◽  
pp. 530-534 ◽  
Author(s):  
J. D. MacLeod ◽  
J. C. G. Laflamme
Keyword(s):  
National Research Council ◽  
Engine Performance ◽  
Application Process ◽  
Turbine Engine ◽  
Coating Application ◽  
Turboprop Engine ◽  
Compressor Performance ◽  
Department Of National Defence ◽  
Project Objectives ◽  
The Impact

In an attempt to increase the time between maintenance actions and to improve performance retention of turboprop engines installed in transport and maritime patrol aircraft, the Canadian Department of National Defence is evaluating an erosion and corrosion-resistant blade coating, for use on compressors. As coatings could appreciably alter engine performance by virtue of their application thickness and surface quality, the National Research Council of Canada was asked to quantify any performance changes that could occur. A project was initiated, utilizing a new Allison T56 turboprop engine, to assess not only the performance changes resulting from the coating, but also those from dismantling and reassembling the compressor, since the compressor must be completely disassembled to apply the coating. This paper describes the project objectives, the experimental installation, and the measured effects of the coating application on compressor performance. Performance variations due to compressor rebuilds on both engine and compressor characteristics are discussed. As the performance changes were small, a rigorous measurement uncertainty analysis is included. The coating application process and the affected overhaul procedures are examined. The results of the pre- and postcoating compressor testing are presented, with a discussion of the impact on engine performance.

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.

Implanted Component Faults and Their Effects on Gas Turbine Engine Performance

1992 ◽  
Vol 114 (2) ◽  
pp. 174-179 ◽  
Author(s):  
J. D. MacLeod ◽  
V. Taylor ◽  
J. C. G. Laflamme
Keyword(s):  
Gas Turbine ◽  
National Research Council ◽  
Engine Performance ◽  
Turbine Rotor ◽  
Gas Turbine Engine ◽  
Tip Clearance ◽  
Turbine Engine ◽  
Turbine Rotor Blade ◽  
Department Of National Defence ◽  
Project Objectives

Under the sponsorship of the Canadian Department of National Defence, the Engine Laboratory of the National Research Council of Canada (NRCC) has established a program for the evaluation of component deterioration on gas turbine engine performance. The effect is aimed at investigating the effects of typical in-service faults on the performance characteristics of each individual engine component. The objective of the program is the development of a generalized fault library, which will be used with fault identification techniques in the field, to reduce unscheduled maintenance. To evaluate the effects of implanted faults on the performance of a single spool engine, such as an Allison T56 turboprop engine, a series of faulted parts were installed. For this paper the following faults were analyzed: (a) first-stage turbine nozzle erosion damage; (b) first-stage turbine rotor blade untwist; (c) compressor seal wear; (d) first and second-stage compressor blade tip clearance increase. This paper describes the project objectives, the experimental installation, and the results of the fault implantation on engine performance. Discussed are performance variations on both engine and component characteristics. As the performance changes were significant, a rigorous measurement uncertainty analysis is included.

Combustor Rebuild Effects on Gas Turbine Performance

1995 ◽  
Author(s):  
J. D. MacLeod ◽  
B. Barry
Keyword(s):  
Gas Turbine ◽  
National Research Council ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Performance Characteristics ◽  
Turbine Engine ◽  
Turbine Performance ◽  
Turboprop Engine ◽  
Project Objectives ◽  
Performance Variations

The Institute for Aerospace Research of the National Research Council of Canada (NRCC), has established a program for the evaluation of component deterioration on gas turbine engine performance. The effort is aimed at investigating the effects of typical in-service faults on the performance characteristics of each individual engine component. As part of this project, a study of the effects of combustor 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 combustor module of a gas turbine engine, and how these changes would influence the results of any component modification testing. To evaluate the effects of rebuilding the combustor on the performance of a single spool engine, such as an Allison T56 turboprop engine, a series of three rebuilds was carried out. This study was performed in a similar way to two previous NRCC studies on the effects of compressor and turbine rebuilding. While the compressor and turbine rebuild studies found performance changes in the order of I% on various engine parameters, the effects of rebuilding the combustor have proven to be of similar magnitude. Based on the results of the combustor 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 combustor rebuilds on engine performance characteristics. As the performance changes were significant, a rigorous measurement uncertainty analysis is included.

Implanted Component Faults and Their Effects on Gas Turbine Engine Performance

1991 ◽  
Author(s):  
J. D. MacLeod ◽  
V. Taylor ◽  
J. C. G. Laflamme
Keyword(s):  
Gas Turbine ◽  
National Research Council ◽  
Engine Performance ◽  
Turbine Rotor ◽  
Gas Turbine Engine ◽  
Tip Clearance ◽  
Turbine Engine ◽  
Turbine Rotor Blade ◽  
Department Of National Defence ◽  
Project Objectives

Under the sponsorship of the Canadian Department of National Defence, the Engine Laboratory of the National Research Council of Canada (NRCC) has established a program for the evaluation of component deterioration on gas turbine engine performance. The effort is aimed at investigating the effects of typical in-service faults on the performance characteristics of each individual engine component. The objective of the program is the development of a generalized fault library which will be used with fault identification techniques in the field, to reduce unscheduled maintenance. To evaluate the effects of implanted faults on the performance of a single spool engine, such as an Allison T56 turboprop engine, a series of faulted parts were installed. For this paper the following faults were analyzed: a) 1st stage turbine nozzle erosion damage, b) 1st stage turbine rotor blade untwist, c) compressor seal wear, d) 1st and 2nd stage compressor blade tip clearance increase. This paper describes the project objectives, the experimental installation, and the results of the fault implantation on engine performance. Discussed are performance variations on both engine and component characteristics. As the performance changes were significant, a rigorous measurement uncertainty analysis is included.

Influence of a Thermal Barrier Coating on the Performance of a Turboprop Engine

1992 ◽  
Author(s):  
J. D. MacLeod ◽  
J. C. G. Laflamme
Keyword(s):  
Surface Roughness ◽  
Thermal Barrier Coating ◽  
Coating Thickness ◽  
Ceramic Coating ◽  
National Research Council ◽  
Engine Performance ◽  
Thermal Barrier ◽  
Barrier Coating ◽  
Project Objectives ◽  
The Impact

Under the sponsorship of the Canadian Department of National Defence, the Engine Laboratory of the National Research Council of Canada has evaluated the influence of applying a thermal barrier coating on the performance of a gas turbine engine. The effort is aimed at quantifying the performance effects of a particular ceramic coating on the first stage turbine vanes. The long term objective of the program is to both assess the relative change in engine performance and compare against the claimed benefits of higher possible turbine inlet temperatures, longer time in service and increased time between overhauls. The engine used for this evaluation was the Allison T56 turboprop with the first stage turbine nozzles coated with the Chromalloy RT-33 ceramic coating. The issues addressed in testing this particular type of hot section coating were; 1) effect of coating thickness on nozzle effective flow area; 2) surface roughness influence on turbine efficiency; This paper describes the project objectives, the experimental installation, and the results of the performance evaluations. Discussed are performance variations due to coating thickness and surface roughness on engine performance characteristics. As the performance changes were small, a rigorous measurement uncertainty analysis is included. The coating application process, and the affected overhaul procedures are examined. The results of the pre- and post-coating turbine testing are presented, with a discussion of the impact on engine performance.

An Alternative Cruising Method (Constant Speed) for the Hercules C-130H: Relative Life Savings When Compared to the Constant Power One and the Effect of Several Engine Physical Faults

2002 ◽  
Author(s):  
Petros Kotsiopoulos ◽  
Riti Singh ◽  
Ioannis Templalexis
Keyword(s):  
Failure Modes ◽  
Operating Cost ◽  
Constant Speed ◽  
Constant Power ◽  
Turbine Engine ◽  
Turboprop Engine ◽  
Prime Concern ◽  
Low Levels ◽  
The Impact ◽  
Engine Life

The total cost to purchase and operate a gas turbine engine is indeed quite substantial. Out of this, the biggest portion is the operating cost. In order to keep it as low as possible, a prime concern is to keep temperatures at the entry of the turbine at low levels. Therefore the effect of engine degradations should be understood and analysed, as well as the impact of the major hot section failure modes. This paper examines an alternative cruising method of constant speed for the Hercules C-130H, powered by the Alison T56-A-15 turboprop engine. This study is being done on a comparative basis to the constant power cruising method, which is applied until now. It is concerning the life savings deduced out of creep. Moreover, the effect of several engine degradations on engine life, for both constant speed and constant power cruising methods has been investigated.

scholarly journals Infrared Thermal Imaging System as a Diagnostic Tool for Gas Turbine Engine Faults

1994 ◽  
Author(s):  
J. D. MacLeod ◽  
P. Steckhan ◽  
D. He
Keyword(s):  
Gas Turbine ◽  
Infrared Thermography ◽  
Imaging System ◽  
National Research Council ◽  
Engine Performance ◽  
Diagnostic Techniques ◽  
Infrared Light ◽  
Infrared Thermal Imaging ◽  
Radiation Spectra ◽  
Project Objectives

With the cost of maintaining a fleet of gas turbine engines continuing to rise, there is a greater need to develop methods to diagnose engine deterioration and identify faulty engine components quickly and efficiently. The Structures, Materials and Propulsion Laboratory of the National Research Council of Canada (NRC) has established a program to develop and evaluate various diagnostic techniques. The effort is aimed at investigating the effects of typical in-service faults on engine performance characteristics. An important aspect of the engine test program is the evaluation of non-intrusive sensors to accurately measure gas turbine performance. Using infrared thermography, the measurement of temperature is accomplished non-intrusively using the infrared radiation spectra. This instrumentation provides an indirect measurement of temperature and does not interfere with the flow field being measured. The temperature patterns can be used to determine engine health, and identify possible fault conditions within the hot section of the engine. This paper describes the project objectives, the experimental installation, and the results of the performance evaluations. A description of the infrared thermography system, and the data reduction and analysis systems used to convert infrared light into temperature profile contours is given.

Validation of a Modified Parallel Compressor Model for Prediction of the Effects of Inlet Swirl on Compressor Performance and Operability

2015 ◽  
Author(s):  
Reginald S. Floyd ◽  
Milton Davis
Keyword(s):  
Pressure Ratio ◽  
Pressure Rise ◽  
Engine Performance ◽  
The United States ◽  
Turbine Engine ◽  
Inlet Distortion ◽  
Inlet Swirl ◽  
Compressor Performance ◽  
Inlet Conditions ◽  
Map Data

Engine inlet distortion complications have plagued the turbine engine development community for decades, and engineers have developed countless methods to identify and combat the harmful effects of inlet distortion. One such type of distortion that has gained much attention in recent years is known as inlet swirl, which results in a significant flow angularity at the face of the engine. This flow angularity can affect the pressure rise and flow capacity of the fan or compressor, and subsequently affect compressor and engine performance. Previous modeling and simulation efforts to predict the effect inlet swirl can have on fan and compressor performance have made great strides, yet still leave a lot to be desired. In particular, a one-dimensional parallel compressor model called DYNTECC (Dynamic Turbine Engine Compressor Code) has been used to analyze the effects of inlet swirl on fan and performance operability of the Honeywell F109 turbofan engine. However, when compared to experimental swirl data gathered at the United States Air Force Academy (USAFA), the model predictions were found to be inaccurate. This paper documents work done to compare the initial predictions generated by DYNTECC to the latest set of experimental swirl data, analyze the potential shortcomings of the initial model, and modify the existing model to more accurately reflect test data. Extensive work was completed to create a methodology that can calibrate the model to existing clean inlet fan map data. In addition, an in depth study of fan/compressor stalling criteria was conducted, and the model was modified to use an alternate stalling criteria that more accurately predicted the point of stall for various swirl inlet conditions. The prediction of the fan stall pressure ratio for all inlet swirl conditions tested is within 2% of the ground test stall point at the same referred fan speed and referred mass flow.

A Fast Gas Turbine Engine Performance Analysis Tool Able to Capture Three Dimensional Effects

2007 ◽  
Author(s):  
Ioannis Templalexis ◽  
Pericles Pilidis ◽  
Vassilios Pachidis ◽  
Petros Kotsiopoulos
Keyword(s):  
Three Dimensional ◽  
Axial Flow ◽  
Engine Performance ◽  
Flow Simulation ◽  
Simulation Method ◽  
Flow Profile ◽  
Flow Distortion ◽  
Performance Simulation ◽  
Turbine Engine ◽  
The Impact

Given the current level of computational resources that are readily available, three dimensional (3-D) gas turbine engine performance simulation remains extremely time consuming. The current paper presents a synthesis of existing flow simulation methods coupled together in the form of a new software package. The software is able to assess the impact of a 3-D flow profile at the intake inlet on engine performance, demanding relatively low computational resources. More precisely four flow simulation techniques are employed, represented respectively by four individual stand alone software sub-modules. 3-D Vortex Lattice Method (VLM) is used to simulate the intake flow. Subsequently the intake outlet 3-D flow profile is decomposed into a radial and a circumferential component. For the compressor performance simulation, that receives those components as inlet boundary conditions, a two dimensional (2-D) Streamline Curvature (SLC) simulation method coupled with an extended parallel compressor model is used. SLC addresses the impact of the radial flow distortion, whereas the extended parallel compressor model examines the impact of circumferential flow distortion on engine performance. The results of the above analysis are stored into an intake-compressor performance characteristic map, which is then fed into a zero dimensional (0-D) performance simulation tool in order to evaluate the overall impact of the intake inlet distorted flow on engine performance. The paper is divided into two major sections. The first one presents the individual flow simulation techniques, together with the corresponding software modules. A short summary of each method is given first and then the software module is described, followed by brief comments on the validation results that have been already published. The section in concluded by the description of the synthesized software. The second major section deals with the application of the synthesized simulation method on a turbojet engine. A generic turbojet engine has been chosen mounted behind a generic intake, given the lack of relevant experimental results. The engine has a four stage axial flow compressor driven by a single stage axial flow turbine, followed by a converging nozzle. 3-D total pressure profiles were imposed at the intake inlet and several comparative graphs of engine’s performance parameters between “clean” and distorted inlet flow conditions are given. The paper is concluded with a discussion on software’s abilities and weaknesses as well as on its potential future expansion.

The Effects of Wet Compression on Gas Turbine Engine Operating Performance

2003 ◽  
Author(s):  
Wayne R. Sexton ◽  
Michael R. Sexton
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
Engine Performance ◽  
Steam Injection ◽  
Performance Characteristics ◽  
Specific Power ◽  
Water Droplets ◽  
Turbine Engine ◽  
Engine Compressor ◽  
Compressor Performance

Water, in the liquid or vapor phase, injected at various locations into the gas turbine cycle has frequently been employed to improve engine performance. One such way to improve engine performance is by steam injection, of varied quantity, into the combustor section of the engine. Combustor steam injection increases turbine mass flow rate without increasing airflow rate and consequently increasing the specific power (power/lbm of air). Another approach, receiving widespread acceptance in recent years, is to inject water droplets into the inlet duct upstream of the engine compressor inlet. As the droplets evaporate, prior to entering the compressor, the inlet air is cooled subsequently decreasing compressor power and thus increasing engine power output. The present paper examines the concept of injecting water droplets, termed fogging, in excess of the amount that can be evaporated before entering the engine compressor. This excess water, termed over-spray, is carried directly into the engine compressor. The computer simulated performance of a simple cycle gas turbine engine using evaporative cooling upstream of the compressor with over-spray is reported. The paper describes an improved simulation model developed to predict compressor performance as water is evaporated while passing through the stages of an axial flow compressor. The effects are similar to those of an intercooled compressor without the complications of additional piping, heat exchangers, and the requirement for a dual spool compressor. The results of a parametric study of the effects of evaporative cooling on engine operating characteristics are presented. These results include compressor performance characteristics modified for various inlet conditions (temperature, pressure, and humidity) and fogging conditions (flow rate, over-spray, and water temperature) as well as estimates of the reduced compression work and lowered compressor discharge temperatures. These modified compressor performance characteristics are used in the engine simulation to predict how an over-sprayed engine would perform under various operating conditions. Estimates of increased output power and increased specific power are presented.

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