Design Considerations and Performance Characteristics of Combustors for Small Gas Turbine Engines

1962 ◽  
Author(s):  
J. M. Haasis
Keyword(s):  
Gas Turbine ◽  
Performance Characteristics ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Considerations ◽  
And Performance

Design Considerations for Nuclear-Aircraft Gas-Turbine Engines

1959 ◽  
Author(s):  
D. R. Riley
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Radiation Level ◽  
Design Considerations ◽  
Nuclear Heating

Many new design considerations are encountered in the design of nuclear aircraft gas-turbine engines. The effect that the power-plant configurations, the cycle, radiation level, residual radiation, and nuclear heating have on the design is discussed in this paper.

Resultant Benefits of Standardized Overhaul Packages for LM2500 Propulsion Gas Turbine Engines in U.S. Navy Applications

2004 ◽  
Author(s):  
Matthew J. Driscoll ◽  
Joseph Picozzi
Keyword(s):  
Gas Turbine ◽  
Condition Based Maintenance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
General Electric ◽  
Turbine Engine ◽  
Gas Generators ◽  
Useful Life ◽  
And Performance ◽  
Unites States

This paper discusses the Unites States Navy’s program to standardize repair and overhaul packages/workscopes for their LM2500 propulsion gas turbine engines. The General Electric LM2500 gas turbine engine is utilized for main propulsion aboard the Navy’s newest surface combatants including the FFG 7, DD 963, CG 47 and DDG 51 class ships. The Navy employs a condition based maintenance philosophy for its fleet of 450 LM2500 engines; removing engines from ships only when in place corrective actions can no longer be effected. Consequently, most LM2500 gas generators and power turbines have exhausted much of their useful life once they arrive at the depot for overhaul. Beginning in 1999, NAVSEA implemented a standardized workscope for these engines to ensure post repair life and performance goals were achieved. This paper discusses the contents of the standardize repair package and the resultant benefits and metrics associated with its execution at both military and commercial facilities.

The influence of effective research and development on the aero engine business

1969 ◽  
Vol 312 (1510) ◽  
pp. 333-347 ◽  
Keyword(s):  
Research And Development ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Capital Equipment ◽  
Aero Engine ◽  
And Performance

The aero engine business is a good example of the growing number of industries whose survival and success depend on their ability to make a success of research. Today’s gas turbine engines are items of capital equipment whose characteristics and performance exert a high leverage on the benefits which its users can achieve. This is because these characteristics critically affect the size and type of aircraft required to perform a particular task. The engine therefore indirectly affects the aircraft price, its drag and the thrust level for which the engine itself has to be sized to match the aircraft’s needs, while its reliability influences the aircraft’s utilization.

Design and Performance Analysis of a Gas Turbine Flameless Combustor Using CFD Simulations

2012 ◽  
Author(s):  
Y. Levy ◽  
F. C. Christo ◽  
I. Gaissinski ◽  
V. Erenburg ◽  
V. Sherbaum
Keyword(s):  
Gas Turbine ◽  
Combustion Regime ◽  
Operating Conditions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Cfd Simulations ◽  
Flow Configurations ◽  
And Performance ◽  
Zone Radius

This study investigates the performance and the conditions under which flameless oxidation can be achieved for a given annular adiabatic combustor. Numerical modelling of velocity, temperature and species fields are performed for different flow configurations of air and methane streams injected into a proposed design of a gas-turbine combustor. Parametric analysis was performed by systematically varying several parameters: radius of a recirculation zone, radius of the combustor, location of air and fuel ports, air and fuel velocities magnitudes and injection angles. The analysis was performed initially using a three-step global chemistry model to identify a design (geometry and operating conditions) that yield flameless combustion regime. The selected design was then modelled using a skeletal (46 reactions) and a detailed (309 reactions) chemical kinetics mechanism. The k–ε turbulence model was used in the most calculations. Overall, similar qualitative flow, temperature, and species patterns were predicted by both kinetics models; however the detailed mechanism provides quantitatively more realistic predictions. An optimal flow configuration was achieved with exhaust NOx emissions of < 7.5 ppm, CO < 35ppm, and a pressure-drop < 5%, hence meeting the design criteria for gas turbine engines. This study demonstrates the feasibility of achieving ultra-low NOx and CO emissions utilising a flameless oxidation regime.

Performance Characteristics of Brush Seals for Limited-Life Engines

1993 ◽  
Vol 115 (2) ◽  
pp. 390-396 ◽  
Author(s):  
R. E. Chupp ◽  
C. A. Dowler
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Performance Characteristics ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Labyrinth Seals ◽  
Performance Improvements ◽  
Limited Life ◽  
In Series ◽  
Brush Seals

Brush seals are potential replacements for air-to-air labyrinth seals in gas turbine engines. An investigation has been conducted to determine the performance characteristics of brush seals for application in limited-life gas turbine engines. An elevated temperature, rotating test rig was designed and built to test labyrinth and brush seals in simulated subsonic and supersonic engine conditions. Results from initial tests for subsonic applications demonstrated that brush seals exhibit appreciably lower leakage compared to labyrinth seals, and thus offer significant engine performance improvements. Performance results have been obtained showing the effect of various brush seal parameters, including: initial interference, backplate gap, and multiple brush seals in series.

Design and Performance Characteristics of Over-Running Clutches in Gas Turbine Drive Applications

1967 ◽  
Vol 89 (2) ◽  
pp. 207-215 ◽  
Author(s):  
R. L. Daniels
Keyword(s):  
Gas Turbine ◽  
Power Transmission ◽  
Subsequent Development ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Know How ◽  
And Performance ◽  
Ancillary Equipment ◽  
Turbine Drive

Ever since the advent of the gas turbine engine, and its subsequent development and sophistication, the very unique operating requirements, characteristics, and benefits of gas turbine engines have challenged engineers of many disciplines to provide ancillary equipment and components that will function successfully with it. This paper will present selected specific examples of gas turbine drive system developments and their related power transmission designs with respect to clutch requirements—the Formsprag area of knowledge, know-how, and competence.

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