Zobrazeno 1 - 7
of 7
pro vyhledávání: '"Davis, Milton W. Jr."'
Autor:
Davis, Milton W. Jr.
A one-dimensional, stage-by-stage axial compression system mathematical model has been constructed which can describe system behavior during post-stall events such as surge and rotating stall. The model uses a numerical technique to solve the nonline
Externí odkaz:
http://hdl.handle.net/10919/50002
Autor:
Rabe, Angela C.
An experimental investigation was conducted in a static ground test facility to determine the flow quality of a serpentine inlet duct incorporating active flow control for several simulated flight conditions. The total pressure distortion at the aero
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=od______2485::8f1159278fa3fc9d039a923964212e22
https://hdl.handle.net/10919/28653
https://hdl.handle.net/10919/28653
Autor:
Boyer, Keith M.
A streamline curvature (SLC) throughflow numerical model was assessed and modified to better approximate the flow fields of highly transonic fans typical of military fighter applications. Specifically, improvements in total pressure loss modeling wer
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=od______2485::7fd0da3275115c63ef36e41ca64fe7b3
http://scholar.lib.vt.edu/theses/available/etd-05032001-113913/
http://scholar.lib.vt.edu/theses/available/etd-05032001-113913/
Autor:
Cousins, William T.
The phenomena of stall and surge in axial-centrifugal compressors is investigated through high-response measurements of both the pressure field and the flowfield throughout the surge cycle. A unique high-response forward-facing and aft-facing probe p
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=od______2485::143682be9a53fb7797494c2b3ca94d60
https://hdl.handle.net/10919/29794
https://hdl.handle.net/10919/29794
Autor:
DiPietro, Anthony Louis
An experimental investigation into the effects of inlet temperature transients on the stall and stall recovery aerodynamics of a low speed multi-stage axial flow compressor has been presented. Experiments were conducted on a low speed multi-stage axi
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=od______2485::9810e68366a412a4012f8b4979f35cef
http://scholar.lib.vt.edu/theses/available/etd-10052007-143638/
http://scholar.lib.vt.edu/theses/available/etd-10052007-143638/
Autor:
Hale, Alan A.
Modem high-performance military aircraft are subjected to rapid flight maneuvers which place great operational demands on their compression system by producing highly distorted flow to the compressor. Inlet distortion generally reduces the engine com
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=od______2485::22b8ffa8e9e091f5c27df0778f928158
http://scholar.lib.vt.edu/theses/available/etd-06062008-154548/
http://scholar.lib.vt.edu/theses/available/etd-06062008-154548/
Autor:
Lindau, Jules Washington
A more robust method for solving the governing equations of a one-dimensional stage-by-stage dynamic compression system model was developed and validated. The improved method was then applied to two-dimensional post-stall models. The improvement in r
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=od______2485::bf8a7f946df234cfaf77fca33c535ab1
http://scholar.lib.vt.edu/theses/available/etd-02132009-171914/
http://scholar.lib.vt.edu/theses/available/etd-02132009-171914/