Performance of an annular turbojet combustor having reduced pressure losses and using propane fuel Page: 4 of 40
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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
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Norgren, Carl T. & Childs, J. Howard. Performance of an annular turbojet combustor having reduced pressure losses and using propane fuel, report, September 24, 1953; (https://digital.library.unt.edu/ark:/67531/metadc59759/m1/4/: accessed March 20, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.