17,005 Documents in our Technical Library
2449539 Total Downloads

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 ...

naca-rm-e8c18

  • Version
  • 60 Downloads
  • 591.24 KB File Size
  • 1 File Count
  • April 21, 2017 Create Date
  • April 21, 2017 Last Updated
Scroll for Details

National Advisory Committee for Aeronautics, Research Memorandum - Preliminary Results of Natural Icing of an Axial Flow Turbojet Engine

A flight investigation is being conducted in natural icing con-
ditions to determine the effect of ice formations on the performance
of an. axial-flow turboJet engine. One fligit was Ends in icing con-
ditionsin which the icing rate varied from 5.1 to 2.1 inches per hour.
During a period of 45 minutes in icing, the tail-pipe temperature
increased from 761° to 10650 F and. the Jet thrust decreased from 1234
to 910 pounds. Ice penetrated to the second-stage stator blades.

No general conclusions can. be reached from these data because
the icing condition was relatively light.

An investigation. in retinal icing conditions is being con-
ducted. at the NAGA Cleveland. laboratory to determine the effect of
ice formation on the pwfornzance of an anal-flow turboaet enane.
Data presented were obtained during one flight at an engine speed
of 9000 rpm. flhis engine speed was chosen because of the low-
operating tail-pipe temperame. Additional data are being obtained
at higher engine speeds am other icing conditions.

The 240-2 turbojet engine was mounted on a four-engine bomber,
which was provided. with anti-icing equipment for the wings, the tail
surfaces, and. the propellers. A general view of the instaJlation is
shown in figure 1. A close-up view of the engine installation is
shown in figure 2. The turboJet engine used for this investigation
has a lO-stage axial-flow compressor, a two-stage turbine, and an
annular combustion chamber.

Instrtmentation was provided at the compressor outlet for cal-
culation of compressor efficiency and at the tail-pipe outlet for
calculations of air flow and thrust. Interstage static pressures
were provided to determine the pressure distribution through the
lO-stage compressor.

Photographs taken after the icing flight are shown in figure 5.
A front view of the ice fomtion on the engine inlet and the starter
housing is shown in figure 5(a). The degree of ice accunmlation on
the engine inlet is indicated in figure 5(b). Ice accumulation on
the inlet guide vanes is shown in figure 5(c). Visual inspection
of the inlet indicated that ice had accumulated. on the first-stage
stator blades (fig. 5(a)), the second-stage stator blades, and the
first-stage rotor blades. Ellie ice formation on the first-stage
rotor blades was concentrated at the leading edge and was approxi-
mately 1/3 inch thick. 'Jhe ice formtion on the second-stage stator
blades was also concentrated at the leading edge and was approxi-
mately 1/52 inch thick and rather sporadic.

FileAction
naca-rm-e8c18 Preliminary Results of Natural Icing of an Axial Flow Turbojet Engine.pdfDownload 

Comment On This Post

Your email address will not be published. Required fields are marked *

naca-rm-e8c18

  • Version
  • 60 Downloads
  • 591.24 KB File Size
  • 1 File Count
  • April 21, 2017 Create Date
  • April 21, 2017 Last Updated
Scroll for Details

National Advisory Committee for Aeronautics, Research Memorandum - Preliminary Results of Natural Icing of an Axial Flow Turbojet Engine

A flight investigation is being conducted in natural icing con-
ditions to determine the effect of ice formations on the performance
of an. axial-flow turboJet engine. One fligit was Ends in icing con-
ditionsin which the icing rate varied from 5.1 to 2.1 inches per hour.
During a period of 45 minutes in icing, the tail-pipe temperature
increased from 761° to 10650 F and. the Jet thrust decreased from 1234
to 910 pounds. Ice penetrated to the second-stage stator blades.

No general conclusions can. be reached from these data because
the icing condition was relatively light.

An investigation. in retinal icing conditions is being con-
ducted. at the NAGA Cleveland. laboratory to determine the effect of
ice formation on the pwfornzance of an anal-flow turboaet enane.
Data presented were obtained during one flight at an engine speed
of 9000 rpm. flhis engine speed was chosen because of the low-
operating tail-pipe temperame. Additional data are being obtained
at higher engine speeds am other icing conditions.

The 240-2 turbojet engine was mounted on a four-engine bomber,
which was provided. with anti-icing equipment for the wings, the tail
surfaces, and. the propellers. A general view of the instaJlation is
shown in figure 1. A close-up view of the engine installation is
shown in figure 2. The turboJet engine used for this investigation
has a lO-stage axial-flow compressor, a two-stage turbine, and an
annular combustion chamber.

Instrtmentation was provided at the compressor outlet for cal-
culation of compressor efficiency and at the tail-pipe outlet for
calculations of air flow and thrust. Interstage static pressures
were provided to determine the pressure distribution through the
lO-stage compressor.

Photographs taken after the icing flight are shown in figure 5.
A front view of the ice fomtion on the engine inlet and the starter
housing is shown in figure 5(a). The degree of ice accunmlation on
the engine inlet is indicated in figure 5(b). Ice accumulation on
the inlet guide vanes is shown in figure 5(c). Visual inspection
of the inlet indicated that ice had accumulated. on the first-stage
stator blades (fig. 5(a)), the second-stage stator blades, and the
first-stage rotor blades. Ellie ice formation on the first-stage
rotor blades was concentrated at the leading edge and was approxi-
mately 1/3 inch thick. 'Jhe ice formtion on the second-stage stator
blades was also concentrated at the leading edge and was approxi-
mately 1/52 inch thick and rather sporadic.

FileAction
naca-rm-e8c18 Preliminary Results of Natural Icing of an Axial Flow Turbojet Engine.pdfDownload 
17,005 Documents in our Technical Library
2449539 Total Downloads

Search The Technical Library

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 ...