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naca-rm-e6l02

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National Advisory Committee for Aeronautics, Research Memorandum - Theoretical Investigation of Thrust Augmentation of Turbojet Engines by Tail Pipe Burning

The take-off thrust of turbojet engines is considerably lower
than that of conventional engine-propeller combinations due to the
low propulsive efficiency of turbojet engines operating at low
airplane velocities. In an attempt to improve the take-off, the
climb, and the high-speed performance of airplanes powered by
turbojet engines, an investigation of various methods of augmenting
the thrust produced by this type of engine is being conducted at
the NACA Cleveland laboratory.

One of the methods being investigated is_tail-pipo burning,
which consists in providing a tail-pipe burner between the turbine.
discharge and the exhaust-nozzle inlet of the turbojet engine. The
tail-pipe burner,_which is located downstream_of the turbine and
therefore does not affect the turbine operating temperature, heats
the turbine exhaust gases to a temperature considerably higher than
would be possible ahead of the turbine because of the temperature
limit imposed by the strength characteristics of the turbine mate-
rials. The increased temperature of the gases at the exhaust-
nozzle inlet results in an increased Jet velocity and therefore
greater thrust. The addition of a tail-pipe burner results in a
decreased total pressure at the exhaust—nozzle inlet caused by
friction losses and momentum pressure loss due to burning. This
decreased total pressure tends to reduce the jet velocity and
therefore to reduce the thrust increase produced by the increased
temperature,

An analysis of this method of augmentation was made to provide
charts from which the performance of a turboJet engine operating
with tail—pipe burning could be conveniently estimated. The charts
and the analysis presented in this report enable the prediction of
the thrust.augmentation produced when the normal Jet velocity, the
tailupipe-burner temperature ratio, and the tail-pipe-burner pres-
sure loss are known. Additional curves are presented for evaluating
the friction pressure losses and momentum pressure loss due to tail-
pipe burning. With the use of the charts, illustrative cases are
calculated and curves that show the effects of airplane velocity,
tail-pipe-burner inlet velocity, tailupipe—diffuser efficiency, and
burner drag coefficient on thrust augmentation are presented. The
effect of tail-pipe burning on the thrust and specific fuel cone
sumption of a turboJet engine operating at various airplane veloci-
ties and for altitudes of sea level and 50,000 feet is computed for
a representative case. The specific fuel cofisumption of thrust aug-
mentation (ratio of change in fuel consumption to change in thrust)
is also presented

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naca-rm-e6l02

  • Version
  • 135 Downloads
  • 1.88 MB File Size
  • 1 File Count
  • March 14, 2017 Create Date
  • March 14, 2017 Last Updated
Scroll for Details

National Advisory Committee for Aeronautics, Research Memorandum - Theoretical Investigation of Thrust Augmentation of Turbojet Engines by Tail Pipe Burning

The take-off thrust of turbojet engines is considerably lower
than that of conventional engine-propeller combinations due to the
low propulsive efficiency of turbojet engines operating at low
airplane velocities. In an attempt to improve the take-off, the
climb, and the high-speed performance of airplanes powered by
turbojet engines, an investigation of various methods of augmenting
the thrust produced by this type of engine is being conducted at
the NACA Cleveland laboratory.

One of the methods being investigated is_tail-pipo burning,
which consists in providing a tail-pipe burner between the turbine.
discharge and the exhaust-nozzle inlet of the turbojet engine. The
tail-pipe burner,_which is located downstream_of the turbine and
therefore does not affect the turbine operating temperature, heats
the turbine exhaust gases to a temperature considerably higher than
would be possible ahead of the turbine because of the temperature
limit imposed by the strength characteristics of the turbine mate-
rials. The increased temperature of the gases at the exhaust-
nozzle inlet results in an increased Jet velocity and therefore
greater thrust. The addition of a tail-pipe burner results in a
decreased total pressure at the exhaust—nozzle inlet caused by
friction losses and momentum pressure loss due to burning. This
decreased total pressure tends to reduce the jet velocity and
therefore to reduce the thrust increase produced by the increased
temperature,

An analysis of this method of augmentation was made to provide
charts from which the performance of a turboJet engine operating
with tail—pipe burning could be conveniently estimated. The charts
and the analysis presented in this report enable the prediction of
the thrust.augmentation produced when the normal Jet velocity, the
tailupipe-burner temperature ratio, and the tail-pipe-burner pres-
sure loss are known. Additional curves are presented for evaluating
the friction pressure losses and momentum pressure loss due to tail-
pipe burning. With the use of the charts, illustrative cases are
calculated and curves that show the effects of airplane velocity,
tail-pipe-burner inlet velocity, tailupipe—diffuser efficiency, and
burner drag coefficient on thrust augmentation are presented. The
effect of tail-pipe burning on the thrust and specific fuel cone
sumption of a turboJet engine operating at various airplane veloci-
ties and for altitudes of sea level and 50,000 feet is computed for
a representative case. The specific fuel cofisumption of thrust aug-
mentation (ratio of change in fuel consumption to change in thrust)
is also presented

FileAction
naca-rm-e6l02 Theoretical Investigation of Thrust Augmentation of Turbojet Engines by Tail Pipe Burning.pdfDownload 
17,005 Documents in our Technical Library
2449510 Total Downloads

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Newest Additions

NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
AA-CP-20212-001
AA-CP-20212-001
ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...