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Engineering Reports, Volume 7, Issue 1, January 2025.Integration of the micro S‐CO2 cycle with V18 MAN 51/60DF engines in powerships for waste heat recovery enhances energy efficiency and sustainability. The system utilizes 374.4 kW of waste heat, achieving 21.8% energy efficiency and 9.7% exergy efficiency, with a net work output of 54.11 kW.
Mehmet Erhan Şahin +2 more
wiley +1 more source
Thermodynamic designing of the small-scale gas turbine engine family with common core
MATEC Web of Conferences, 2018 The paper describes the method of selecting the working process parameters of a family of small-scale gas turbine engines (GTE) with common core. As an example, the thermodynamic design of a family of small-scale gas turbine engines (SGTE) with common ...
Tkachenko Andrey +3 more
doaj +1 more source
Gas turbine exhaust nozzle [PDF]
, 1973 An elongated hollow string is disposed in an exhaust nozzle combustion chamber and communicates with an air source through hollow struts at one end. The other end of the string is bell-mouth shaped and extends over the front portion of a nozzle plug. The
Straight, D. M.
core +1 more source
A remote augmentor lift system with a turbine bypass engine [PDF]
Two supersonic vertical takeoff or landing (VTOL) aircraft engine types, a conventional medium bypass ratio turbofan, and a turbine bypass turbojet were studied. The aircraft assumed was a clipped delta wing with canard configuration.
Fishbach, L. H., Franciscus, L. C.
core +1 more source
Pollution reduction technology program for small jet aircraft engines: Class T1 [PDF]
, 1977 Small jet aircraft engines (EPA class T1, turbojet and turbofan engines of less than 35.6 kN thrust) were evaluated with the objective of attaining emissions reduction consistent with performance constraints.
Bruce, T. W. +2 more
core +1 more source
Aviation, 2019 Micro turbojets can be used for propulsion of civilian and military aircraft, consequently their investigation and control is essential. Although these power plants exhibit nonlinear behaviour, their control can be based on linearized mathematical models
Khaoula Derbel, Károly Beneda
doaj +1 more source
Identification and dual adaptive control of a turbojet engine [PDF]
The objective of this paper is to utilize the design methods of modern control theory to realize a dual-adaptive feedback control unit for a highly nonlinear single spool airbreathing turbojet engine.
Leininger, G., Merrill, W.
core +1 more source
Investigation of the stall-induced shock wave (hammershock) at the inlet to the engine [PDF]
The peak static pressures measured at the inlet to the engine during stall are presented for a turbojet and two turbofan engines. It is shown for one turbofan and the turbojet that the static pressure ratio across the hammershock does not exceed ...
Kurkov, A. P. +2 more
core +1 more source
Initial Flow Matching Results of MHD Energy Bypass on a Supersonic Turbojet Engine Using the Numerical Propulsion System Simulation (NPSS) Environment [PDF]
, 2010 Preliminary flow matching has been demonstrated for a MHD energy bypass system on a supersonic turbojet engine. The Numerical Propulsion System Simulation (NPSS) environment was used to perform a thermodynamic cycle analysis to properly match the flows ...
Benyo, Theresa L.
core +1 more source
Impulse Correlation for Partially Filled Detonation Tubes [PDF]
, 2004 The effect of nozzles on the impulse obtained from a detonation tube of circular cross section has been the focus of many experimental and numerical studies. In these cases, the simplified detonation tube is closed at one end (forming the thrust surface)
Cooper, M., Schauer, F., Shepherd, J. E.
core +1 more source