Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers Page: 2 of 44
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
rINASA Technical U
Ml li:a llIAllli
NACA RM E2B08 3 11768 01436 0003
NATIONAL AIVISGRY COMMITTEE FOR AERONAUBICS
0OMPONXNT AND 0VER-ATL PERFORMANCE EVALUATION OF AN ATAL-FXW
TURBOJXET ENGINE OVER A RANG OF ENGlhE-fILET
By Curtis L. alker, B. C. Huntley
ani W. M. Braithwaite
An investigation was conducted in an altitude test chamber at the
NADA Lewis laboratory to evaluate the performance of an axial-flow
turbojet engine over a range of engine-inlet Reynolds numbers.' The
range of Reynolds numbers investigated provided data which were appli-
cable over a range of altitudes from 10,000 to 50,000 feet at a flight
Mach number of 0.7; 100 percent ram-pressure recovery was assumed.
Reducing the engine inlet Reynolds number resulted in a reduction
of corrected air flow and compressor efficiency but did not affect the
compressor pressure ratio at a given corrected engine speed. The
decreased compressor efficiency required an increase in turbine power
that resulted in an increase in exhaust-gas total temperature.
Combustion efficiency is presented as a function of a combustion
parameter. At low values of this parameter, which corresponded to low
Reynolds number operation for this investigation, combustion efficiency
decreased very rapidly. As a result of the combined effects of decreased
compressor efficiency and combustion efficiency, the reduction in engine-
inlet Reynolds number resulted in an increased fuel flow. At rated cor-
rected engine speed this increase was about 12 percent.
A method is presented whereby conventional performance variables
such as net thrust and specific fuel consumption may be obtained. for
any flight condition within the range of Reynolds numbers investigated.
The increased exhaus t-gas temperature caused an increase in tail-pipe
total pressure which offset the decrease in corrected air flow and thus
produced a generalization of the thrust parameter.
In previous altitude-performance evaluations (for example, refer-
enoe l), data were obtained over a range of altitudes and flight Mach
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Walker, Curtis L.; Huntley, S. C. & Braithwaite, W. M. Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers, report, July 10, 1952; (digital.library.unt.edu/ark:/67531/metadc59177/m1/2/: accessed January 20, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.