Performance of an annular turbojet combustor having reduced pressure losses and using propane fuel Page: 4 of 40
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:
NACA RM E53G24
The combustor installation (fig. 1) was similar to that of refer-
ence 1. The combustor-inlet and combustor-outlet ducts were connected
to the laboratory air supply and low-pressure exhaust systems, respec-
tively. Air-flow rates and combustor pressures were regulated by remote-
0 controlled valves located upstream and downstream of the combustor. The
O desired combustor-inlet air temperature was obtained by means of an
electric air preheater.
Air flow was metered by a concentric-hole, sharp-edge orifice in-
stalled according to A.S.M.E. specifications. The vapor fuel-flow rate
was metered by a calibrated sharp-edge orifice. Thermocouples and pres-
sure tubes were located at the combustor-inlet and outlet stations indi-
cated in figure 1. The number, type, and position of these instruments
at each of the three stations are indicated in figure 2. The combustor-
outlet thermocouples and outlet total-pressure probes were located at
centers of equal areas in the duct. Manifolded upstream total-pressure
probes (station 1) and downstream static-pressure probes (station 3) were
connected to absolute manometers; individual downstream total- and
static-pressure probes were connected to banks of differential manom-
eters. The chromel-alumel thermocouples (station 2) were connected to a
self-balancing recording potentiometer.
The fuel used in this investigation was vaporized commercial propane
supplied from the laboratory distribution system.
A total of 13 combustor configurations was investigated. Each com-
bustor consisted of a one-quarter segment (900) of a single-annular com-
bustor having an outside diameter of 25.5 inches, an inside diameter of
10.6 inches, and a length from fuel injectors to combustor-outlet ther-
mocouples (station 2) of approximately 25 inches. The maximum combustor
cross-sectional area was 105 square inches (corresponding to 420 sq in.
for the complete combustor). A longitudinal cross-sectional view of the
combustor is shown in figure 3, and a three-quarter cutaway view with the
final liner configuration in figure 4.
Each combustor was given a numerical designation to indicate the
liner configuration, followed by a letter designating the fuel injector
design. Five equally spaced 7/64-inch orifices (corresponding to 20
orifices in the complete combustor) injected the propane fuel downstream
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.
Norgren, Carl T. & Childs, J. Howard. Performance of an annular turbojet combustor having reduced pressure losses and using propane fuel, report, September 24, 1953; (digital.library.unt.edu/ark:/67531/metadc59759/m1/4/: accessed December 14, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.