Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions /

Performance of a modular combustor designed for a VTOL tip-turbine lift fan /

Marchionna, Nicholas R.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

Prepared by Lewis Research Center."November 1971."--Cover.Major NASA subject terms: Combustion chamb...

Performance of inlet stage of transonic compressor /

Urasek, Donald C.
Lewis, George W., Jr.
Steinke, Ronald J.
Lewis Research Center.

January 1976

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 /

Bowditch, David N.
Tabata, William K.
Anderson, Bernhard H.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Performance of a 48-module swirl-can turbojet combustor segment at high temperatures using ASTM-A1 fuel /

Niedzwiecki, Richard W.
Moyer, Harry M.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

Performance of turbojet swirl module combustor segment at high temperatures.Prepared at Lewis Resear...

Turbojet combustor performance with natural gas fuel

Marchionna, Nicholas R.
Trout, Arthur M.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

Prepared at Lewis Research Center."February 1970."Cover title.Includes bibliographical references (p...

Idle efficiency and pollution results for two-row swirl-can combustors having 72 modules /

Biaglow, James A.
Trout, Arthur M.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 9).Mode of acc...

Effect of diffuser bleed on performance of an annular swirl can combustor /

Juhasz, Albert J.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 12).Mode of ac...

Performance of experimental channeled-wall annular turbojet combustor at conditions simulating high-altitude supersonic flight.

Zettle, Eugene V.
Friedman, Robert, 1929-
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1955

"March 15, 1955."Includes bibliographical references (p. 7).Mode of access: Internet

Performance investigation of can-type combustor from British turbojet engine and comparison of this combustor with can-type combustor from U.S. turbojet engine /

Cook, William P.
Koch, Richard G., joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "February 28, 1950."Includes bibliographical references (p. 11).Mode of access: Inte...

Cruise performance of an isolated 1.15 pressure ratio turbofan propulsion system simulator at Mach numbers from 0.6 to 0.85 /

Steffen, Fred W.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 22).Mode of ac...

Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions

Moyer, H. M.
Butze, H. F.
Trout, A. M.

January 1969

Evaluating performance of swirl can turbojet combustor at simulated supersonic inlet condition

Dispersion of turbojet engine exhaust in flight /

Holdeman, James D.
Lewis Research Center.

January 1973

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 15).Mode of ac...

Exhaust pollutant emissions from swirl-can combustor module arrays at parametric test conditions /

Mularz, Edward J.
Verbulecz, Peter W.
Wear, Jerrold D.
U.S. Army Air Mobility Research and Development Laboratory.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center and the U.S. Army Air Mobility R&D Laboratory.Cover title.Includes...

Performance of a hydrogen burner to simulate air entering scramjet combustors /

Russin, William Roger.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 21).Mode of ...

Performance of vortex generators in a Mach 2.5 low-bleed full-scale 45-percent-internal-contraction axisymmetric inlet /

Neumann, Harvey E.
Shaw, Robert J. (Robert Joseph), 1946-
Wasserbauer, Joseph F.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

Performance of a modular combustor designed for a VTOL tip-turbine lift fan /

Marchionna, Nicholas R.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

Prepared by Lewis Research Center."November 1971."--Cover.Major NASA subject terms: Combustion chamb...

Performance of inlet stage of transonic compressor /

Urasek, Donald C.
Lewis, George W., Jr.
Steinke, Ronald J.
Lewis Research Center.

January 1976

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 /

Bowditch, David N.
Tabata, William K.
Anderson, Bernhard H.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Performance of a 48-module swirl-can turbojet combustor segment at high temperatures using ASTM-A1 fuel /

Niedzwiecki, Richard W.
Moyer, Harry M.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

Performance of turbojet swirl module combustor segment at high temperatures.Prepared at Lewis Resear...

Turbojet combustor performance with natural gas fuel

Marchionna, Nicholas R.
Trout, Arthur M.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

Prepared at Lewis Research Center."February 1970."Cover title.Includes bibliographical references (p...

Idle efficiency and pollution results for two-row swirl-can combustors having 72 modules /

Biaglow, James A.
Trout, Arthur M.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 9).Mode of acc...

Effect of diffuser bleed on performance of an annular swirl can combustor /

Juhasz, Albert J.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 12).Mode of ac...

Performance of experimental channeled-wall annular turbojet combustor at conditions simulating high-altitude supersonic flight.

Zettle, Eugene V.
Friedman, Robert, 1929-
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1955

"March 15, 1955."Includes bibliographical references (p. 7).Mode of access: Internet

Performance investigation of can-type combustor from British turbojet engine and comparison of this combustor with can-type combustor from U.S. turbojet engine /

Cook, William P.
Koch, Richard G., joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "February 28, 1950."Includes bibliographical references (p. 11).Mode of access: Inte...

Cruise performance of an isolated 1.15 pressure ratio turbofan propulsion system simulator at Mach numbers from 0.6 to 0.85 /

Steffen, Fred W.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 22).Mode of ac...

Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions

Moyer, H. M.
Butze, H. F.
Trout, A. M.

January 1969

Evaluating performance of swirl can turbojet combustor at simulated supersonic inlet condition

Dispersion of turbojet engine exhaust in flight /

Holdeman, James D.
Lewis Research Center.

January 1973

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 15).Mode of ac...

Exhaust pollutant emissions from swirl-can combustor module arrays at parametric test conditions /

Mularz, Edward J.
Verbulecz, Peter W.
Wear, Jerrold D.
U.S. Army Air Mobility Research and Development Laboratory.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center and the U.S. Army Air Mobility R&D Laboratory.Cover title.Includes...

Performance of a hydrogen burner to simulate air entering scramjet combustors /

Russin, William Roger.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 21).Mode of ...

Performance of vortex generators in a Mach 2.5 low-bleed full-scale 45-percent-internal-contraction axisymmetric inlet /

Neumann, Harvey E.
Shaw, Robert J. (Robert Joseph), 1946-
Wasserbauer, Joseph F.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

Performance of a modular combustor designed for a VTOL tip-turbine lift fan /

Marchionna, Nicholas R.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

Prepared by Lewis Research Center."November 1971."--Cover.Major NASA subject terms: Combustion chamb...

Performance of inlet stage of transonic compressor /

Urasek, Donald C.
Lewis, George W., Jr.
Steinke, Ronald J.
Lewis Research Center.

January 1976

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 /

Bowditch, David N.
Tabata, William K.
Anderson, Bernhard H.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions /

Abstract

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Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions /

Abstract

Extracted data

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