The Potential Impact of Multiplane-Multispeed Balancing on Gas Turbine Production and Overhaul Costs

1975 ◽  
Vol 97 (3) ◽  
pp. 347-353 ◽  
Author(s):  
R. H. Badgley
Keyword(s):  
Gas Turbine ◽  
Cost Effective ◽  
Gas Turbine Engine ◽  
Single Step ◽  
Potential Cost ◽  
Turbine Engine ◽  
Critical Speeds ◽  
Cost Effective Method ◽  
Bearing Assembly ◽  
Potential Impact

This paper describes recent advances in the development of a practical, cost-effective method for balancing, in a single step, a final shaft-bearing assembly simultaneously in a number of planes and at a number of speeds. This method is capable of overcoming assembly-introduced unbalance, and will permit rotor operation through critical speeds in which component elastic axis bending occurs. Detailed results of test efforts are presented in order to illustrate the effectiveness of the method. The procedure by which the method may be applied to gas turbine engine shafts, and the potential cost advantages expected to accrue therefrom, are described and discussed.

The Potential Impact of Future Fuels on Small Gas Turbine Engines

1982 ◽  
Author(s):  
J. A. Saintsbury ◽  
P. Sampath
Keyword(s):  
Gas Turbine ◽  
Operating Experience ◽  
Gas Turbine Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
The Future ◽  
Potential Impact ◽  
The Impact ◽  
Whitney Aircraft

The impact of potential aviation gas turbine fuels available in the near to midterm, is reviewed with particular reference to the small aviation gas turbine engine. The future course of gas turbine combustion R&D, and the probable need for compromise in fuels and engine technology, is also discussed. Operating experience to date on Pratt & Whitney Aircraft of Canada PT6 engines, with fuels not currently considered of aviation quality, is reported.

Real-Time Virtual Sensing of Component Damage Variables in a Gas Turbine Engine

2017 ◽  
Author(s):  
Juan-Pablo Afman ◽  
J. V. R. Prasad ◽  
Stephen Antolovich
Keyword(s):  
Real Time ◽  
Gas Turbine ◽  
Financial Incentive ◽  
Cost Effective ◽  
Gas Turbine Engine ◽  
Operational Environment ◽  
Virtual Sensors ◽  
Turbine Engine ◽  
Effective Manner ◽  
Engine Maintenance

Accurate life prediction and monitoring for gas turbine engines has become increasingly important in recent years as commercial aircraft fleets are being offered through guaranteed engine maintenance programs, where plan rates are based on mission profiles, operating environment, operational hours and cycles accumulated. Hence, accurate monitoring and life predictions of critical engine components is associated with a tremendous financial incentive. A state of the art gas turbine engine carries up to 5000 sensors, which can be used to evaluate the performance of the engine. This data can be used to monitor engines in real-time, as well as collecting and analyzing that data after being streamed via satellite during flight, where algorithms can evaluate and prevent technical issues before they occur. The data collected provides engine manufacturers with early warnings related to failure diagnosis, and it enables airlines to schedule engine maintenance efficiently and in a cost effective manner. Due to the nature of the engine’s operational environment, sensors cannot be placed in certain areas of interest inside a gas turbine engine. Furthermore, thermo-mechanical models are often complex and computationally expensive to run in real time. Hence, in this work we describe the development of thermo-mechanical reduced models that can act as virtual sensors, in locations where real sensors cannot survive, and hence approximate damage variables at critical locations on a component of interest, which can be used for real-time diagnostics.

Application of an Advanced Hybrid Rotordynamics Model to the Complete Structure of a Marine Gas Turbine Engine

1988 ◽  
Vol 110 (4) ◽  
pp. 578-584 ◽  
Author(s):  
B. D. Thompson ◽  
R. H. Badgley
Keyword(s):  
Gas Turbine ◽  
Structural Response ◽  
Gas Turbine Engine ◽  
Mode Shapes ◽  
Structural Flexibility ◽  
Turbine Engine ◽  
Critical Speeds ◽  
Structural Support ◽  
Engine Vibration ◽  
Vibration Problems

Extensive fleet experience with the LM2500 marine gas turbine engine has identified it as an engine that exhibits wear-accelerating vibration effects. The critical speeds and associated mode shapes were not well understood by U.S. Navy engineers. To help deal with vibration-related problems, an analytical model was developed to calculate engine rotordynamic and structural response. The procedure is a multilevel, multirotor hybrid extension of the classical Myklestad-Prohl method. Presented herein are some of the model’s predictions, and correlations with actual engine vibration measurements. The model predicted in excess of 20 different critical speeds in the engine’s operating range. Because of the engine’s structural flexibility, most of the critical speeds were engine casing and structural support resonances, driven by imbalance or misalignment in one or both of the engine rotors. Rotor-bending critical speeds were found to be strongly influenced by engine casing and support structure stiffness and mass. Using the model’s predicted mode shapes, new mounting locations for accelerometers could be selected to determine vibration severity at various frequencies better. This has given the U. S. Navy new insights into fleet vibration problems, and provides a useful tool for achieving reduced engine removals.

scholarly journals A Design Approach for a Practical Turbojet Engine Combustor Diffuser System

1984 ◽  
Author(s):  
T. L. DuBell ◽  
P. L. Russell ◽  
R. S. Reilly
Keyword(s):  
Gas Turbine ◽  
Cost Effective ◽  
Gas Turbine Engine ◽  
Design Approach ◽  
Combustion System ◽  
Excellent Performance ◽  
Turbine Engine ◽  
Stable Combustion ◽  
Discharge Velocity ◽  
Propulsive Power

The combustion system in a gas turbine engine is the source of the energy released to produce propulsive power. Maintaining stable combustion and achieving good performance requires controlled introduction of air and good mixing in the combustor. The compressor discharge velocity must be reduced by diffusing the air before it reaches the combustor. There are fundamental and practical limits on how much diffusion can be done, and parasitic loss of pressure is introduced. This paper describes an approach to achieving an improved, cost effective diffuser design. The diffuser that results provides excellent performance, is simple, and is dynamically stable.

Design Optimization Study of Isolation Mount Systems for Gas Turbine Engine Accessories

2005 ◽  
Author(s):  
William Sheridan ◽  
Kazem Kazerounian
Keyword(s):  
Design Optimization ◽  
Gas Turbine ◽  
Cost Effective ◽  
Gas Turbine Engine ◽  
Optimization Techniques ◽  
Optimization Process ◽  
Element Analysis ◽  
Isolation System ◽  
Turbine Engine ◽  
Effective Manner

Design optimization has become increasingly important in today’s world. The ability to develop products that offer the best possible solution, distinguish industry leaders from those that lag behind. To reach this goal, optimization techniques are required which provide solutions in a timely and cost effective manner. This paper addresses a specific optimization process for designing isolation mount systems for gas turbine engine accessory components. This process enables the designer to quickly select an isolation system that will reduce the loads on components without the use of a time consuming Finite Element Analysis (FEA). Commercially available tools such as MATLAB [7] and MSC-WORKING MODEL 2D [6] are used to study a range of mount systems and help the designer focus his attention on the best choice of design variables. Gas Turbine engine accessory mount systems are generally sized by emergency conditions such as Fan Blade Out (FBO). These emergency conditions are rarely seen in service, but since they can drive the cost and weight of the mount system, an optimization process is needed to select the best configurations. References [8] through [10] discuss this in detail. Design Cycle time is just as important as cost and weight. The ability to size and package components quickly and accurately is vital to the design process. Poor utilization of space can drive cost and weight as much as poor component design. Knowing the correct size of the mount system in a rapid fashion offers further opportunities for surrounding components & systems to be optimized.

Flexible manufacturing in repair of gas turbine engine components

1992 ◽  
Author(s):  
KIRK D ◽  
ANDREW VAVRECK ◽  
ERIC LITTLE ◽  
LESLIE JOHNSON ◽  
BRETT SAYLOR
Keyword(s):  
Gas Turbine ◽  
Flexible Manufacturing ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Components
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