Study of oxygenated ecofuel applications in CI engine, gas turbine, and jet engine

2019 ◽  
pp. 405-441 ◽  
Author(s):  
Niraj Kumar
Keyword(s):  
Gas Turbine ◽  
Jet Engine ◽  
Ci Engine

CM-R 411

Alloy Digest ◽  
1967 ◽  
Vol 16 (9) ◽  
Keyword(s):  
Shear Strength ◽  
High Temperature ◽  
Gas Turbine ◽  
Precipitation Hardening ◽  
Base Alloy ◽  
Heat Treating ◽  
Nickel Base Alloy ◽  
Jet Engine ◽  
Temperature Performance ◽  
Nickel Base

Abstract CM-R41 is a vacuum-melted, precipitation hardening nickel-base alloy possessing outstanding properties in the temperature range of 1200 F to 1800 F. It is recommended for jet engine and gas turbine components operating at high temperatures. This datasheet provides information on composition, physical properties, elasticity, tensile properties, and shear strength as well as creep. It also includes information on high temperature performance as well as forming, heat treating, machining, and joining. Filing Code: Ni-127. Producer or source: Cannon-Muskegon Corporation.

CARPENTER M-252

Alloy Digest ◽  
1973 ◽  
Vol 22 (9) ◽  
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Physical Properties ◽  
Gas Turbine ◽  
Base Alloy ◽  
Heat Treating ◽  
Nickel Base Alloy ◽  
Jet Engine ◽  
Temperature Performance ◽  
Nickel Base

Abstract CARPENTER M-252 is an age-hardenable nickel-base alloy designed for highly stressed parts operating at temperatures up to 1600 F. Its prime application is for jet-engine and gas-turbine buckets. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, machining, and joining. Filing Code: Ni-195. Producer or source: Carpenter.

CMN-155

Alloy Digest ◽  
1968 ◽  
Vol 17 (8) ◽  
Keyword(s):  
High Temperature ◽  
Heat Resistance ◽  
Physical Properties ◽  
Gas Turbine ◽  
Base Alloy ◽  
Heat Treating ◽  
Jet Engine ◽  
Iron Base Alloy ◽  
Temperature Performance ◽  
High Oxidation

Abstract CMN-155 is an austenitic iron-base alloy having high oxidation and heat resistance combined with good high temperature properties. It is recommended for jet engine and gas turbine components, high temperature fasteners, and rocket chambers. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as creep. It also includes information on high temperature performance as well as forming, heat treating, machining, and joining. Filing Code: SS-212. Producer or source: Cannon-Muskegon Corporation.

Transformation of an Aviation Turboshaft Engine Into a Experimental Jet Engine for Laboratory Testing Unstable Radial Compressor Work

2014 ◽  
Author(s):  
Marián Hocko ◽  
Jiri Polansky
Keyword(s):  
Gas Turbine ◽  
Experimental Testing ◽  
Thermodynamic Characteristics ◽  
Power Generator ◽  
Jet Engine ◽  
Radial Compressor ◽  
Laboratory Device ◽  
Research And Education ◽  
Turboshaft Engine ◽  
Electronic Elements

The article deals with the use of a small aviation turboshaft engine for laboratory purposes. This study describes its transformation into an experimental device for research and education. Various constructional, technological and controlling modifications and settings of the gas turbine test stand were carried out and tested on a stationary configuration. The stationary system can be used as a small backup power generator or as a drive unit for a compressor, pump, etc. New control systems, electronic elements and methods of measuring rotations, pressure and temperature are tested for educational and research purposes. The study includes a schematic description of modelling measurements and subsequent numerical evaluation of the thermodynamic characteristics of the cycle in an experimental gas turbine. The laboratory device presented here is, thanks to technological, material and thermodynamic research, suitable for educating and testing the knowledge of future aviation and mechanical engineers. The content of the article is a description of the use of transformed small turboshaft engine into small jet engine by means of experimental testing of unstable work of the radial compressor under laboratory conditions.

Mixing of Exhaust and By-pass Flow in a By-pass Engine

1962 ◽  
Vol 66 (620) ◽  
pp. 528-530 ◽  
Author(s):  
H. Pearson
Keyword(s):  
Gas Turbine ◽  
Combustion Temperature ◽  
Propulsive Efficiency ◽  
Jet Engine ◽  
Equivalent Result ◽  
Jet Velocity ◽  
Cycle Efficiency

It is well known that the main purpose of the by-pass principle is to improve the propulsive efficiency of a simple jet engine by removing some of the energy left in the jet gases and using this to compress an extra quantity of air, known as the by-pass air, this air being ejected rearwards with the jet gases. In this way a greater mass of air is ejected rearwards at a lower jet velocity and thus a better propulsive efficiency is obtained. This is an extremely simplified view of the advantages of the by-pass engine, however, since an equivalent result of obtaining a lower jet velocity can be obtained by designing the jet engine for a lower combustion temperature. The by-pass principle is of advantage because it enables a higher propulsive efficiency to be obtained at the same time as employing a high combustion temperature and therefore a high basic cycle efficiency. If the component efficiencies of a gas turbine were 100 per cent, cycle efficiency would not depend upon combustion temperature at all, and there would thus be no advantage in principle in using the by-pass engine. In practice there would probably be some residual advantage left in that for a given thrust a lower engine weight could be obtained.

The United States Navy “Standard Day” for Marine Gas Turbines

2017 ◽  
Author(s):  
John Hartranft ◽  
Bruce Thompson ◽  
Dan Groghan
Keyword(s):  
United States ◽  
Gas Turbine ◽  
United States Navy ◽  
Gas Turbines ◽  
The United States ◽  
Industrial Applications ◽  
Jet Engines ◽  
Jet Engine ◽  
Advantages And Disadvantages ◽  
Power Capability

Following the successful development of aircraft jet engines during World War II (WWII), the United States Navy began exploring the advantages of gas turbine engines for ship and boat propulsion. Early development soon focused on aircraft derivative (aero derivative) gas turbines for use in the United States Navy (USN) Fleet rather than engines developed specifically for marine and industrial applications due to poor results from a few of the early marine and industrial developments. Some of the new commercial jet engine powered aircraft that had emerged at the time were the Boeing 707 and the Douglas DC-8. It was from these early aircraft engine successes (both commercial and military) that engine cores such as the JT4-FT4 and others became available for USN ship and boat programs. The task of adapting the jet engine to the marine environment turned out to be a substantial task because USN ships were operated in a completely different environment than that of aircraft which caused different forms of turbine corrosion than that seen in aircraft jet engines. Furthermore, shipboard engines were expected to perform tens of thousands of hours before overhaul compared with a few thousand hours mean time between overhaul usually experienced in aircraft applications. To address the concerns of shipboard applications, standards were created for marine gas turbine shipboard qualification and installation. One of those standards was the development of a USN Standard Day for gas turbines. This paper addresses the topic of a Navy Standard Day as it relates to the introduction of marine gas turbines into the United States Navy Fleet and why it differs from other rating approaches. Lastly, this paper will address examples of issues encountered with early requirements and whether current requirements for the Navy Standard Day should be changed. Concerning other rating approaches, the paper will also address the issue of using an International Organization for Standardization, that is, an International Standard Day. It is important to address an ISO STD DAY because many original equipment manufacturers and commercial operators prefer to rate their aero derivative gas turbines based on an ISO STD DAY with no losses. The argument is that the ISO approach fully utilizes the power capability of the engine. This paper will discuss the advantages and disadvantages of the ISO STD DAY approach and how the USN STD DAY approach has benefitted the USN. For the future, with the advance of engine controllers and electronics, utilizing some of the features of an ISO STD DAY approach may be possible while maintaining the advantages of the USN STD DAY.

Production of Medium Chain Fatty Acid Ethyl Ester, Combustion, and Its Gas emission using a Small-Scale Gas Turbine Jet Engine

2019 ◽  
Vol 16 (14) ◽  
pp. 1304-1316
Author(s):  
Nhan Thi Thuc Truong ◽  
Arnupong Suttichaiya ◽  
Wikanda Hiamhoen ◽  
Peerapat Thinnongwaeng ◽  
Chaloemkwan Ariyawong ◽  
...  
Keyword(s):  
Fatty Acid ◽  
Gas Turbine ◽  
Ethyl Ester ◽  
Acid Ethyl Ester ◽  
Fatty Acid Ethyl Ester ◽  
Chain Fatty Acid ◽  
Small Scale ◽  
Gas Emission ◽  
Jet Engine ◽  
Medium Chain

Stall Control

1960 ◽  
Author(s):  
S. Drabek
Keyword(s):  
Gas Turbine ◽  
General Problem ◽  
The Other ◽  
Jet Engine ◽  
Other Hand ◽  
Stall Control

Compressor stall has had an increasing effect through the years upon gas turbine controls. The general problem was reasonably well known in the first decade of jet engine history after the “Whittle Engine”. The scheduling approach to the control of compressor stall established during this time has become rooted throughout the industry. On the other hand, an idealized approach based on sensing incipient stall remains an intriguing challenge.

Advanced Test Cell Diagnostics for Gas Turbine Engines (USAF Automated Jet Engine Test Strategy – AJETS)

2001 ◽  
Author(s):  
Michael J. Roemer ◽  
Gregory J. Kacprzynski ◽  
Michael Schoeller ◽  
Ron Howe ◽  
Richard Friend
Keyword(s):  
Anomaly Detection ◽  
Real Time ◽  
Gas Turbine ◽  
Test Cell ◽  
Engine Test ◽  
Jet Engine ◽  
Test Strategy ◽  
Post Test ◽  
Test Cells ◽  
And Performance

Improved test cell diagnostics capable of detecting and classifying engine mechanical and performance faults as well as instrumentation problems is critical to reducing engine operating and maintenance costs while optimizing test cell effectiveness. Proven anomaly detection and fault classification techniques utilizing engine Gas Path Analysis (GPA) and statistical/empirical models of structural and performance related engine areas can now be implemented for real-time and post-test diagnostic assessments. Integration and implementation of these proven technologies into existing USAF engine test cells presents a great opportunity to significantly improve existing engine test cell capabilities to better meet today’s challenges. A suite of advanced diagnostic and troubleshooting tools have recently been developed and implemented for gas turbine engine test cells as part of the Automated Jet Engine Test Strategy (AJETS) program. AJETS is an innovative USAF program for improving existing engine test cells by providing more efficient and advanced monitoring, diagnostic and troubleshooting capabilities. This paper describes the basic design features of the AJETS system; including the associated data network, sensor validation and anomaly detection/diagnostic software that was implemented in both a real-time and post-test analysis mode. These advanced design features of AJETS are currently being evaluated and advanced utilizing data from TF39 test cell installations at Travis AFB and Dover AFB.

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