Temat: micro-turbine - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Mass model of microgasturbine single spool turbojet engine
Autorzy:: Czarnecki, M.
Powiązania:: https://bibliotekanauki.pl/articles/247344.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine
micro gas turbine
mass model
Schreckling
turbojet
Opis:: Presented paper consists detailed mass model of micro gas turbine single spool turbojet in well-known Scheckling design layout (1R/1A). One of major criteria in aviation is weight that is granted by airworthiness requirements. At present, exempt from certification process are RC airplanes or UAV with total take-off weight less than 22.5 kg. From the 70's mass model was added as a part of aero engines design process. Engine weight affects airplane or UAV weight greatly, because it is a source of variety structure loads. Weight reduction efficiency factor, verifying in terms of design quality a micro gas turbine, and the flying object as a system. Developed computational model allows to estimate weight of the components (gas generator shaft, compressor rotor, compressor diffuser, combustor, turbine nozzle, turbine rotor, jet pipe, casings and housings) and whole engine as well. Model inputs are related to technological axisymmetric dimensions obtained from thermo gas dynamic and construction equations, making it easy to use. Obtained results was presented for several micro gas turbines (mSO1-designed by author, FD3-64, TK-50, JF-50, MW-54, KJ-66, AMT Olympus). Advantage of this model allows to avoid time consuming CAD modelling process at design study level. Presented algorithm can be used also in the design of UAV as well as issues related to the preliminary multidisciplinary design and optimization PMDO cases.
Źródło:: Journal of KONES; 2013, 20, 1; 49-54
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Design-point, off-design meanline performance analysis and CFD computations of the axial turbine to micro gasturbine engine
Autorzy:: Bar, W.
Czarnecki, M.
Powiązania:: https://bibliotekanauki.pl/articles/245777.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: turbine
gasturbine
axial turbine
micro
CFD
Opis:: Presented paper consists detailed analysis of the turbine to micro gasturbine. Calculatios was made for axial turbine with given mass flow rate m=0.15 [kg/s] and total inlet temperature T3*=950 [K]. The results of Design-Point, Off-Design Meanline Performance analysis and CFD computation are presented. The differences between typical size gasturbine turbines and turbines to micro-gasturbines are highlighted and some guidelines for designers of microgasturbines are given. As a major conclusions for designers of microgasturbines there is a considerations that require to be very carefull and forewarn that typical corelations for commercial gas turbines could't be take it as granted. In particular, compression ratio — solution possibility, micro gasturbine rotor speed,turbine expansion ratio Pi T as a function of compressor and turbine efficiency, efficiency of turbine as a function of reynolds number for constant specific speed coefficient and constant specific diameter coefficient,turbine to micro gasturbine performance map for different normalized rotational speed, 2D and 3D contour plots of entropy, relative Mach number at middle cut of the blade, static pressure at middle cut of the blade are presented in the paper.
Źródło:: Journal of KONES; 2009, 16, 4; 9-16
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Identification of design parameters for microgasturbine engines
Autorzy:: Czarnecki, M.
Powiązania:: https://bibliotekanauki.pl/articles/242372.pdf
Data publikacji:: 2015
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: turbine engines
gasturbine
micro
propulsion
Opis:: The research object consists study of simplified turbojet engine known as a Schreckling design. Simplified layout is related to single centrifugal compressor and single axial turbine design (1R-1T). Presented design is favoured in model gasturbines that uses common compressor rotor from automotive turbochargers. Input data for further calculations was obtained from Garret turbo systems compressor performance maps. Total pressure and total to static stage efficiency was assumed from map of contours at maximum stage efficiency. Additional data from database allowed determining outer diameter and rotational speed of the compressor rotor. Collected data was applied to gasturbine thermogasdynamics model. Decision variables: mass flow rate from 0.1-0.8 [kg/s] range, and exhaust gas temperature from 800-1200 [K] range was taken into account. Turbine expansion ratio was calculated with thermo-mechanical coupling conditions for engine continuous operation. Calculated engine thrust and specific fuel consumption was presented in reference to AMT Netherlands microgasturbine range. Presented results allow to rapid identification of design parameters at early stage of design Obtained results allow to omit thermogasdynamics calculations and focus on the design of the individual engine components. Number of computational models is reduced by 20-30% in reference to given assumptions.
Źródło:: Journal of KONES; 2015, 22, 4; 79-85
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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