scholarly journals Sensor and Actuator Needs for More Intelligent Gas Turbine Engines

2010 ◽  
Author(s):  
Sanjay Garg ◽  
Klaus Schadow ◽  
Wolfgang Horn ◽  
Hugo Pfoertner ◽  
Ion Stiharu
Keyword(s):  
Gas Turbine ◽  
State Of The Art ◽  
Life Time ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Defense Acquisition ◽  
Sensors And Actuators ◽  
Efficient Operation ◽  
Aerospace Research ◽  
Advanced Technologies

This paper provides an overview of the controls and diagnostics technologies, that are seen as critical for more intelligent gas turbine engines (GTE), with an emphasis on the sensor and actuator technologies that need to be developed for the controls and diagnostics implementation. The objective of the paper is to help the “Customers” of advanced technologies, defense acquisition and aerospace research agencies, understand the state-of-the-art of intelligent GTE technologies, and help the “Researchers” and “Technology Developers” for GTE sensors and actuators identify what technologies need to be developed to enable the “Intelligent GTE” concepts and focus their research efforts on closing the technology gap. To keep the effort manageable, the focus of the paper is on “On-Board Intelligence” to enable safe and efficient operation of the engine over its life time, with an emphasis on gas path performance.

Inlet Fogging of Gas Turbine Engines: Part A — Theory, Psychrometrics and Fog Generation

2000 ◽  
Author(s):  
Cyrus B. Meher-Homji ◽  
Thomas R. Mee
Keyword(s):  
Gas Turbine ◽  
Air Temperature ◽  
Gas Turbines ◽  
State Of The Art ◽  
Ambient Air ◽  
Process Industry ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Strong Function ◽  
Turbine Output

Gas Turbine output is a strong function of the ambient air temperature with power output dropping by 0.3–0.5 % for every 1°F rise in ambient temperature. This loss in output presents a significant problem to utilities, cogenerators and IPPs when electric demands are high during the hot months. In the petrochemical and process industry, the reduction in output of mechanical drive gas turbines curtails plant output. One way to counter this drop in output is to cool the inlet air. The paper contrasts the traditional evaporative cooling technique with direct inlet fogging. The state of the art relating to fog generation and psychrometrics of inlet fogging are described.

Working Group Activities of AGARD Propulsion and Energetics Panel

1993 ◽  
Author(s):  
Ahmet S. Ucer
Keyword(s):  
Gas Turbine ◽  
Working Group ◽  
State Of The Art ◽  
The State ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Specific Topic ◽  
Experimental Knowledge ◽  
Group Activities ◽  
Working Groups

One of the major activities of AGARD Panels is to form working groups which assemble experts who work on the particular subject for two or three years. As a result of the work an Advisory Report is published which compiles the state of the art knowledge on the chosen specific topic. This paper explains the philosophy and procedures adopted during the formation of working groups of the Propulsion and Energetics Panel. Working groups concerning gas turbine technologies are presented. The selected working groups aim to improve the computational and experimental knowledge which would lead to the design of advanced aero gas turbine engines. Objective, scope, procedure, and important results of each Working Group will be explained. Working groups which were active during 1980’s and which are presently active are covered.

Conversion of Sulfur Dioxide to Sulfur Trioxide in Gas Turbine Exhaust

1990 ◽  
Vol 112 (4) ◽  
pp. 585-589 ◽  
Author(s):  
B. W. Harris
Keyword(s):  
Gas Turbine ◽  
Life Time ◽  
Combined Cycle ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Boiler Tubes ◽  
Cycle Systems ◽  
Marine Diesel ◽  
Gas Turbine Exhaust ◽  
Turbine Exhaust

Acid dewpoints were calculated from SO2-to-SO3 conversion in gas turbine exhaust. These data can be used as guidelines in setting feedwater temperatures in combined-cycle systems. Accurate settings can prevent corrosion of heat-exchanger (boiler) tubes, thus extending their life time. This study was done using gas turbine engines and a laboratory generator set. The units burned marine diesel or diesel No. 2 fuel with sulfur contents up to 1.3 percent. The exhaust from these systems contained an excess of 20 percent oxygen, and 3–10 percent water vapor. Exhaust temperatures ranged from 728 to 893 K (455 to 620°C).

scholarly journals Gas Turbine Condition Monitoring and Prognosis: A Review

2011 ◽  
Vol 2-3 ◽  
pp. 694-699
Author(s):  
Sha Sha Wang ◽  
Wei Min Wang ◽  
Yong Qiang Shi ◽  
Ya Zhang
Keyword(s):  
Mechanical System ◽  
Gas Turbine ◽  
Condition Monitoring ◽  
Future Development ◽  
State Of The Art ◽  
Maintenance Cost ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Heavy Vehicles ◽  
Industrial Plants

Gas-turbine engines are critical to the operation of most industrial plants, aircraft and heavy vehicles. Condition monitoring is essential to mastering mechanical system running status, improving operation reliability, and reducing maintenance cost. This paper reviews state-of-the-art gas turbine condition monitoring, puts forward the pending problems and predicts future development in the field. Three main advanced methods are introduced briefly in the end.

Production of Integrally-Cast Airfoil Components for Small Gas-Turbine Engines

1962 ◽  
Author(s):  
J. H. Boyle
Keyword(s):  
Gas Turbine ◽  
Present State ◽  
Investment Casting ◽  
State Of The Art ◽  
Casting Process ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Pattern Production ◽  
Final Inspection

This paper presents a review of the progress made by the investment casting foundries in producing integrally-cast airfoil components for small gas-turbine engines. The casting process, from pattern production to the final inspection operations, is discussed in detail. Suggested dimensional tolerances, based on the present state of the art, are included. Finally, the properties and casting characteristics of various alloys commonly used for internal components are presented.

The Effect of Stagger Variability in Gas Turbine Fan Assemblies

2006 ◽  
Vol 129 (2) ◽  
pp. 404-411 ◽  
Author(s):  
Mark J. Wilson ◽  
Mehmet Imregun ◽  
Abdulnaser I. Sayma
Keyword(s):  
Gas Turbine ◽  
State Of The Art ◽  
Turbine Engines ◽  
Manufacturing Processes ◽  
Gas Turbine Engines ◽  
Aeroelastic Model ◽  
Fan Blade ◽  
Geometric Variation ◽  
Bypass Ratio ◽  
Noise Production

Fan blades of high bypass ratio gas turbine engines are subject to substantial aerodynamic and centrifugal loads, producing the well-known phenomenon of fan blade untwist. The accurate prediction of the running geometry, as opposed to the cold geometry at rest, is crucial in the assessment of aerodynamic performance, vibratory response, and noise production of the fan. The situation is further complicated by the fact that some geometric variation is inevitable even for the state-of-the-art manufacturing processes used. The aim of this paper is to investigate the effect of static stagger variability on the dynamic untwist behavior of fan assemblies. An aeroelastic model was used to show that under certain conditions the stagger pattern changes significantly, both in form and amplitude, relative to the static configuration. At other conditions, a strong correlation between the running and static patterns is demonstrated.

Working Group Activities of AGARD Propulsion and Energetics Panel

1994 ◽  
Vol 116 (2) ◽  
pp. 307-314
Author(s):  
A. S. Ucer
Keyword(s):  
Gas Turbine ◽  
Working Group ◽  
State Of The Art ◽  
The State ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Specific Topic ◽  
Experimental Knowledge ◽  
Group Activities ◽  
Working Groups

One of the major activities of AGARD panels is to form working groups, which assemble experts who work on the particular subject for two or three years. As a result of the work, an advisory report is published, which compiles the state-of-the-art knowledge on the chosen specific topic. This paper explains the philosophy and procedures adopted during the formation of working groups of the Propulsion and Energetics Panel. Working groups concerning gas turbine technologies are presented. The selected working groups aim to improve the computational and experimental knowledge that would lead to the design of advanced aero gas turbine engines. Objective, scope, procedure, and important results of each working group will be explained. Working groups that were active during the 1980s and which were presently active are covered.

The Effect of Stagger Variability in Gas Turbine Fan Assemblies

2006 ◽  
Author(s):  
Mark J. Wilson ◽  
Mehmet Imregun ◽  
Abdulnaser I. Sayma
Keyword(s):  
Gas Turbine ◽  
State Of The Art ◽  
Turbine Engines ◽  
Manufacturing Processes ◽  
Gas Turbine Engines ◽  
Aeroelastic Model ◽  
Fan Blade ◽  
Geometric Variation ◽  
Bypass Ratio ◽  
Noise Production

Fan blades of high bypass ratio gas turbine engines are subject to substantial aerodynamic and centrifugal loads, producing the well-known phenomenon of fan blade untwist. The accurate prediction of the running geometry, as opposed to the cold geometry at rest, is crucial in the assessment of aerodynamic performance, vibratory response and noise production of the fan. The situation is further complicated by the fact that some geometric variation is inevitable even for the state-of-the-art manufacturing processes used. The aim of this paper is to investigate the effect of static stagger variability on the dynamic untwist behaviour of fan assemblies. An aeroelastic model was used to show that under certain conditions the stagger pattern changes significantly, both in form and amplitude, relative to the static configuration. At other conditions, a strong correlation between the running and static patterns is demonstrated.

Compressor Turbine Vane Ring (PT6 Engine) Repair Development

1987 ◽  
Author(s):  
N. Sourial
Keyword(s):  
Gas Turbine ◽  
State Of The Art ◽  
Aerospace Industry ◽  
Turbine Engines ◽  
Economic Factors ◽  
Gas Turbine Engines ◽  
Replacement Cost ◽  
Competitive Edge ◽  
Turbine Vane ◽  
The Individual

In today’s aerospace industry there is a trend, which was probably started by economic factors, to donate more time and effort establishing viable salvage repairs of high priced items. This not only creates a competitive edge for the individual who initiates the repair but also stimulates industry to utilize other conceptions or improvements of existing techniques. This paper will deal with one such item which for some years was considered “unrepairable” due to the complexity of its design. The compressor turbine vane ring in the PT6 Engine was selected because it is located in the heart of the engine. It is subjected to a very severe environment and damages occuring to it are a common problem in all gas turbine engines. Consequently this repair, which brings the part back to its new condition for a fraction of the replacement cost, involves a great deal of state of the art technology.

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