scholarly journals Advanced Technology for Reducing Aircraft Engine Pollution

1974 ◽  
Vol 96 (4) ◽  
pp. 1354-1360 ◽  
Author(s):  
R. E. Jones
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Advanced Technology ◽  
Turbine Engines ◽  
Variable Geometry ◽  
Gas Turbine Engines ◽  
Large Reduction ◽  
Final Phase ◽  
Fuel Staging ◽  
Develop Technology

The proposed EPA regulations covering emissions of gas turbine engines will require extensive combustor development. The NASA is working to develop technology to meet these goals through a wide variety of combustor research programs conducted in-house, by contract, and by university grant. In-house efforts using the swirl-can modular combustor have demonstrated sizable reduction in NOx emission levels. Testing to reduce idle pollutants has included the modification of duplex fuel nozzles to air-assisted nozzles and an exploration of the potential improvements possible with combustors using fuel staging and variable geometry. The Experimental Clean Combustor Program, a large contracted effort, is devoted to the testing and development of combustor concepts designed to achieve a large reduction in the levels of all emissions. This effort is planned to be conducted in three phases with the final phase to be an engine demonstration of the best reduced emission concepts.

Practical Implications of Integrating Turbomachinery Into the Air Turborocket

2004 ◽  
Author(s):  
Joshua A. Clough ◽  
Mark J. Lewis
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Launch Vehicle ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Space Launch ◽  
Practical Implications

The development of new reusable space launch vehicle concepts has lead to the need for more advanced engine cycles. Many two-stage vehicle concepts rely on advanced gas turbine engines that can propel the first stage of the launch vehicle from a runway up to Mach 5 or faster. One prospective engine for these vehicles is the Air Turborocket (ATR). The ATR is an innovative aircraft engine flowpath that is intended to extend the operating range of a conventional gas turbine engine. This is done by moving the turbine out of the core engine flow, alleviating the traditional limit on the turbine inlet temperature. This paper presents the analysis of an ATR engine for a reusable space launch vehicle and some of the practical problems that will be encountered in the development of this engine.

scholarly journals The Advanced Low-Emissions Catalytic-Combustor Program: Phase I — Description and Status

1979 ◽  
Author(s):  
A. J. Szaniszlo
Keyword(s):  
Phase I ◽  
Gas Turbine ◽  
Primary Objective ◽  
Pollutant Emission ◽  
Turbine Engines ◽  
Variable Geometry ◽  
Gas Turbine Engines ◽  
Analytical Evaluation ◽  
Three Phase ◽  
Catalytic Combustor

The Advanced Low-Emissions Catalytic-Combustor Program ia an ongoing three-phase contract contract effort with the primary objective of evolving the technology required for incorporating catalytic combustors into advanced aircraft gas-turbine engines. Phase I is corrently in progress. At the present time, analytical evaluation is being conducted on advanced catalytic combustor concepts — including variable geometry — with their known inherent potential advantages of low level pollutant emission, widened combustion at ability limits, and reduced pattern factor for longer turbine life. Phases II and III will consist of experimental evaluation of the most promising concepts.

scholarly journals A Simple Variable-Geometry Combustor for the Automotive-Turbine Engine

1976 ◽  
Author(s):  
R. M. Schirmer
Keyword(s):  
Gas Turbine ◽  
Swirling Flow ◽  
Turbine Engines ◽  
Variable Geometry ◽  
Gas Turbine Engines ◽  
Engine Emissions ◽  
Turbine Engine ◽  
Geometry Configuration ◽  
Mixing Rates ◽  
Statutory Limit

A combustor utilizing concepts of swirling flow and orifices in order to optimize mixing rates was developed for application in low-emissions automotive gas turbine engines. Low emissions were obtained at one operating condition with a fixed-geometry configuration. Addition of a variable opening in the dome of the combustor provided low emissions over the expected operating range for an automotive gas turbine engine. Emissions of NOx obtained on a simulated Federal driving cycle were near the Federal statutory limit, and emissions of CO and HC were considerably lower.

Closed Gas Turbine Engines for Future Marine Propulsion

1976 ◽  
Vol 13 (03) ◽  
pp. 309-314
Author(s):  
F. Critelli ◽  
A. Pietsch ◽  
N. Spicer
Keyword(s):  
Gas Turbine ◽  
New Technology ◽  
Operating Cost ◽  
Advanced Technology ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Closed Cycle ◽  
Turbine Engine ◽  
Excellent Opportunity ◽  
Marine Propulsion

The Maritime Administration, in its pursuit of improved economics and advanced technology, initiated a study which would evaluate new marine powerplants. It became quite apparent for several sound technical reasons that the closed-cycle gas turbine engine afforded an excellent opportunity for achievement of Mar-Ad's goal. This paper addresses the new-technology engine as applied to maritime ships, illustrating the advantages to shipowners and operators. Efficiency, multifuel capability, installation flexibility, reduction in ship's manning, as well as the overall reduced operating cost are highlighted in this paper.

The Testing and Approval of Aircraft Engine Mounted Accessories

1982 ◽  
Vol 196 (1) ◽  
pp. 57-64
Author(s):  
D S Pearson
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Single Frequency ◽  
Turbine Engines ◽  
Severity Assessment ◽  
Gas Turbine Engines ◽  
Shaft Speed ◽  
Unified Approach ◽  
Frequency Excitation ◽  
Environmental Simulation

Vibration measurements on gas turbine engines are normally made using accelerometers. The environment to which engine accessories would be subject has been evaluated by comparing ‘g’ peaks in the frequency spectrum, individually, with empirical yardsticks of severity. Endurance approval testing of accessories to withstand the environment so characterized is normally conducted by applying unidirectional single frequency excitation to simulate engine conditions at a particular shaft speed. These procedures have proved inadequate in predicting failure or verifying corrective measures where accessory problems due to wear phenomena are concerned. This paper analyses reasons for this inadequacy in terms of measurement practice, engine severity assessment, environmental simulation and approval procedures. By recognizing the effect of multi-frequency vibration in three planes it further aims to provide a unified approach to accessory design and development by which service accessory reliability might be improved. Although at first sight more expensive, the approach described will in many cases reduce to previous practice. In cases where greater test expenditure is necessary, loopholes will have been plugged by which many expensive service problems previously escaped.

scholarly journals Cobalt–Niobium-Carbide Eutectic Alloys for Increasing the Service Life of Gas Turbine Engines

2021 ◽  
Vol 22 (4) ◽  
pp. 678-693
Author(s):  
G. P. Dmitrieva ◽  
T. S. Cherepova ◽  
T. V. Pryadko
Keyword(s):  
Service Life ◽  
Gas Turbine ◽  
Niobium Carbide ◽  
Aircraft Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Eutectic Alloys ◽  
Heat Resistant ◽  
The Creation

This article represents the stages of the creation of new serial wear-proof and heat-resistant (at temperatures up to 1100 °C) cobalt–Nb-carbide cast eutectic alloys of the KhTN (XTN) grade at the G.V. Kurdyumov Institute for Metal Physics of the N.A.S. of Ukraine, comparing them by their main properties, and use in aircraft engine engineering.

scholarly journals Integration of On-Line and Off-Line Diagnostic Algorithms for Aircraft Engine Health Management

2007 ◽  
Author(s):  
Takahisa Kobayashi ◽  
Donald L. Simon
Keyword(s):  
Gas Turbine ◽  
Health Management ◽  
Diagnostic Algorithm ◽  
Aircraft Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Simulation Environment ◽  
Diagnostic Algorithms ◽  
Engine Model ◽  
On Line

This paper investigates the integration of on-line and off-line diagnostic algorithms for aircraft gas turbine engines. The on-line diagnostic algorithm is designed for in-flight fault detection. It continuously monitors engine outputs for anomalous signatures induced by faults. The off-line diagnostic algorithm is designed to track engine health degradation over the lifetime of an engine. It estimates engine health degradation periodically over the course of the engine’s life. The estimate generated by the off-line algorithm is used to “update” the on-line algorithm. Through this integration, the on-line algorithm becomes aware of engine health degradation, and its effectiveness to detect faults can be maintained while the engine continues to degrade. The benefit of this integration is investigated in a simulation environment using a nonlinear engine model.

scholarly journals Analysis and directions of technological and organization problem updating in gas turbine aircraft engine repair

2020 ◽  
Vol 2020 (8) ◽  
pp. 42-48
Author(s):  
Vyacheslav Bezyazychnyy ◽  
Andrey Smirnov
Keyword(s):  
Gas Turbine ◽  
New Technologies ◽  
Aircraft Engine ◽  
Technical State ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Technology Application ◽  
Organization Problem ◽  
Repair Techniques

There are presented technological (requirements in new technologies for repair of gas turbine engines (GTE) repaired according to a technical state, growing requirements on reliability, high cost of repair, a limited access to new technologies) and organization (absence of repair localization, high competition etc.) problems of aircraft gas turbine engine repair. The direction for updating: development of new repair technologies at the transition to the concept of repair on a technical state; module technology application; repair production localization; creation of flexible repair techniques etc. is considered.

Observed Rotordynamic Phenomena in Aircraft Gas Turbine Development

2015 ◽  
Author(s):  
Fredric F. Ehrich
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Nonlinear Effects ◽  
Aircraft Engine ◽  
Tip Clearance ◽  
Resonant Peak ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Nonlinear Responses ◽  
Remedial Actions

Observations, analysis and understanding of out-of-the-ordinary rotordynamic phenomena (including several instabilities and nonlinear responses) observed in aircraft gas turbine engines and other high-speed rotating machinery over the course of the author’s career in the design and development of aircraft gas turbine engines are described. Some observed phenomena were already widely recognized in the rotordynamic community such as: • Hysteretic whirl • The tip clearance effect on stability of turbomachinery rotors • Instability due to trapped liquids in the rotor • Hysteresis in the resonant peak amplitude • Effective suppression of rotor instability by anisotropy in the engine support structure Other observations were fairly new to the field of rotordynamics at that time they were observed but were identified as being new manifestations of vibration phenomena already familiar to vibration technologists in fields other than high-speed rotordynamics such as: • Sum-and-difference frequency response • Relaxation oscillations • Nonlinear effects of anisotropic clearance in roller and gas bearings At that time these phenomena were observed, the pressure for remediation of the problems they represented in the context of ongoing aircraft engine development resulted in intense attention and analysis which, in turn, often resulted in new insights, useful diagnoses, and effective remedial actions.

Fabrication of Fe-36Ni Alloy Powder from its Scrap

2013 ◽  
Vol 747 ◽  
pp. 619-622
Author(s):  
Jung Yeul Yun ◽  
Shun Myung Shin ◽  
Dong Won Lee ◽  
Jong Nam Kim ◽  
Jei Pil Wang
Keyword(s):  
High Temperature ◽  
Elevated Temperature ◽  
Gas Turbine ◽  
Alloy Powder ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Turbine Engines ◽  
Temperature Structure ◽  
Gas Turbine Engines ◽  
Elevated Temperature Strength

Ni-based superalloys are used extensively in the hot section of gas turbine engines owing to their inherent elevated temperature strength and creep resistance. As such, aircraft engine manufactures are continually striving to push the envelope of the capabilities of such high temperature structure materials in order to increase both engine performance and efficiency [1,2].

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