Fundamentals of Jet Propulsion with Applications

Flack, Ronald D.

doi:10.1017/cbo9780511807138

Cited by 93 publications

(40 citation statements)

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“… The flame in the combustor shouldn't be prone to flame out;  Minimal weight and volume [7]. Minimal pressure loss is one of the basic requirements of any gas turbine combustor.…”

Section: Main Reqirements In the Design Of Combusturmentioning

confidence: 99%

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Gas Turbine Engine Combustors and the Estimation of Their Pressure Loss

Varga¹,

ÓVÁRI²,

Kavas³

2017

AFASES 2017

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“… The flame in the combustor shouldn't be prone to flame out;  Minimal weight and volume [7]. Minimal pressure loss is one of the basic requirements of any gas turbine combustor.…”

Section: Main Reqirements In the Design Of Combusturmentioning

confidence: 99%

“…The total temperature in the exit section is 1148 K [6]. Length and the effective diameter of the chosen combustor are respectively 0.34 m and 0.086 m. The estimated friction coefficient is 0.04 [7]. We are interested in the ratio of exit total pressure and inlet total pressure.…”

Section: Using Fanno Line Flow To Calculate the Friction Caused Pressmentioning

confidence: 99%

Gas Turbine Engine Combustors and the Estimation of Their Pressure Loss

Varga¹,

ÓVÁRI²,

Kavas³

2017

AFASES 2017

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“…All processes in the ideal turbojet cycle are assumed to be reversible. The net work per unit mass of the ideal Brayton cycle is expressed as a function of temperatures at each stage in the thermodynamic cycle for constant [17]:…”

Section: Fundamentals Of Turbojet Operationmentioning

confidence: 99%

Development and Validation of an NPSS Model of a Small Turbojet Engine

Vannoy¹,

Cadou²

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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Recent studies have shown that integrated gas turbine engine (GT)/solid oxide fuel cell (SOFC) systems for combined propulsion and power on aircraft offer a promising method for more efficient onboard electrical power generation. However, it appears that nobody has actually attempted to construct a hybrid GT/SOFC prototype for combined propulsion and electrical power generation. This thesis contributes to this ambition by developing an experimentally validated thermodynamic model of a small gas turbine (~230 N thrust) platform for a bench-scale GT/SOFC system. The thermodynamic model is implemented in a NASA-developed software environment called Numerical Propulsion System Simulation (NPSS). An indoor test facility was constructed to measure the engine's performance parameters: thrust, air flow rate, fuel flow rate, engine speed (RPM), and all axial stage stagnation temperatures and pressures. The NPSS model predictions are compared to the measured performance parameters for steady state engine operation.

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“…Sir Frank Whittle patented his gas turbine engine in 1930 and after several years of development, a version of the same was first installed on an aircraft in 1941 [2]. Hans von Ohain had a patent for his engine in Germany in 1936 and the first flight with this engine had taken place in 1939 [2].…”

Section: The Birth Ofturbine Engine Control Systemsmentioning

confidence: 99%

“…Hans von Ohain had a patent for his engine in Germany in 1936 and the first flight with this engine had taken place in 1939 [2]. The first gas turbine engine developed by Whittle [2] had a simple throttle lever that controlled fuel flow into the engine. To accommodate the functional requirements when fitted on aircraft, design of fuel control system had to take into account effects of altitude, temperature and forward speed [3].…”

Section: The Birth Ofturbine Engine Control Systemsmentioning

confidence: 99%

Aircraft turbine engine control systems development: Historical perspective

Lutambo

Wang

Yue

et al. 2015

2015 34th Chinese Control Conference (CCC)

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This paper describes the development of aircraft turbine engine control systems from the historical point of view to the present. With the increasing emphasis on aircraft safety, enhanced performance, and affordability, as well as the need to reduce the environmental effect caused by aircraft, there are many new challenges being faced by the designers of aircraft propulsion systems. The paper provides an overview of the various technological development activities in aircraft engine control and diagnostics, both current and some accomplished in the recent past. The motivations for each of the research efforts, the research approach, technical challenges, and the key progress to date are summarized.

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Fundamentals of Jet Propulsion with Applications

Cited by 93 publications

References 0 publications

Gas Turbine Engine Combustors and the Estimation of Their Pressure Loss

Gas Turbine Engine Combustors and the Estimation of Their Pressure Loss

Development and Validation of an NPSS Model of a Small Turbojet Engine

Aircraft turbine engine control systems development: Historical perspective

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