Ask
Search
My library
ORKG

ORKG Ask

Our mission is to organize scholarly knowledge and make it accessible to humans and machines.

About

About ORKG Ask
Report issue
Statistics
Contact

Legal

Terms of use
Data protection (sheet)
Imprint
Accessibility
License

Technical

We
open source
System status
Changelog
Frontend: v1.41.0
Backend: v1.13.4

We use cookies to provide a better user experience.

Data Protection

Conversion of an experimental turbojet combustor from ASTM A-1 fuel to natural gas fuel

Humenik, F. M.

Publication date

March 1971

Language

English

Abstract

Conversion of experimental turbojet combustor from ASTM A-1 fuel to natural gas fue

Extracted data

Related items

High-Pressure Combustion Testing Reveals Promise of Low-Emission Combustors for Advanced Subsonic Gas Turbines

Lyons, Valerie J.

March 1997

NASA Lewis Research Center's new, world-class, 60-atm combustor research facility, the Advanced Subs...

Research Data Acquired in World-Class, 60-atm Subsonic Combustion Rig

Lee, Chi-Ming
Wey, Changlie

April 1999

NASA Lewis Research Center's new, world-class, 60-atmosphere (atm) combustor research facility, the ...

Evaluation of an experimental short-length annular combustor: One-side-entry dilution airflow concept

Biaglow, J. A.
Humenik, F. M.

March 1973

A test program was conducted to evaluate an experimental short-length annular combustor that uses a ...

Comparison of ASTM-A1 and natural gas fuels in an annular turbojet combustor

Perkins, P. J.
Wear, J. D.
Schultz, D. F.

October 1969

Comparison of ASTM-A1 liquid fuel and natural gas fuels in annular turbojet combustor at Mach

Performance gains by using heated natural-gas fuel in an annular turbojet combustor

Marchionna, N. R.

March 1973

A full-scale annular turbojet combustor was tested with natural gas fuel heated from ambient tempera...

Comparison of combustion characteristics of ASTM A-1, propane, and natural-gas fuels in an annular turbojet combustor

Jones, R. E.
Wear, J. D.

January 1973

The performance of an annular turbojet combustor using natural-gas fuel is compared with that obtain...

Performance of a turbojet combustor using natural gas fuel heated to 1200⁰ F (922 K)

Fear, James S.
Tacina, Robert R.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Combustion efficiency was determined using natural gas fuel over a range of injection temperatures ...

Effect of increased fuel temperature on emissions of oxides of nitrogen from a gas turbine combustor burning ASTM jet-A fuel

Marchionna, N. R.

January 1974

An annular gas turbine combustor was tested with heated ASTM Jet-A fuel to determine the effect of i...

Effects of fuel nozzle design on performance of an experimental annular combustor using natural gas fuel

Wear, J. D.
Schultz, D. F.

November 1972

Tests of various fuel nozzles were conducted with natural gas fuel in a full-annulus combustor. The ...

Combustor technology for future aircraft

Tacina, Robert R.

January 1990

The continuing improvement of aircraft gas turbine engine operating efficiencies involves increases ...

Effect of increased fuel temperature on emissions of oxides of nitrogen from a gas turbine combustor burning natural gas

Marchionna, N. R.

December 1973

An annular gas turbine combustor was tested with heated natural gas fuel to determine the effect of ...

Development of a short-length turbojet combustor Summary report, 3 Jun. 1965 - 18 Apr. 1967

Kitts, D. L.

March 1968

Performance tests of short length, gas turbine combustors with atomized or vaporized fuel injectio

Effects of prevaporized fuel on exhaust emissions of an experimental gas turbine combustor

Ingebo, R. D.
Norgren, C. T.

January 1973

Effects of fuel vaporization on the exhaust emission levels of oxides of nitrogen (NOX), carbon mono...

Broad specification fuels combustion technology program

Dodds, W. J.
Ekstedt, E. E.

January 1984

Design and development efforts to evolve promising aircraft gas turbine combustor configurations for...

Performance of a short modular turbojet combustor segment using ASTM-A1 fuel [electronic resource] /

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

A 27-inch (68.6-cm) long rectangular combustor segment consisting of an array of 48 combustor module...

High-Pressure Combustion Testing Reveals Promise of Low-Emission Combustors for Advanced Subsonic Gas Turbines

Lyons, Valerie J.

March 1997

NASA Lewis Research Center's new, world-class, 60-atm combustor research facility, the Advanced Subs...

Research Data Acquired in World-Class, 60-atm Subsonic Combustion Rig

Lee, Chi-Ming
Wey, Changlie

April 1999

NASA Lewis Research Center's new, world-class, 60-atmosphere (atm) combustor research facility, the ...

Evaluation of an experimental short-length annular combustor: One-side-entry dilution airflow concept

Biaglow, J. A.
Humenik, F. M.

March 1973

A test program was conducted to evaluate an experimental short-length annular combustor that uses a ...

Comparison of ASTM-A1 and natural gas fuels in an annular turbojet combustor

Perkins, P. J.
Wear, J. D.
Schultz, D. F.

October 1969

Comparison of ASTM-A1 liquid fuel and natural gas fuels in annular turbojet combustor at Mach

Performance gains by using heated natural-gas fuel in an annular turbojet combustor

Marchionna, N. R.

March 1973

A full-scale annular turbojet combustor was tested with natural gas fuel heated from ambient tempera...

Comparison of combustion characteristics of ASTM A-1, propane, and natural-gas fuels in an annular turbojet combustor

Jones, R. E.
Wear, J. D.

January 1973

The performance of an annular turbojet combustor using natural-gas fuel is compared with that obtain...

Performance of a turbojet combustor using natural gas fuel heated to 1200⁰ F (922 K)

Fear, James S.
Tacina, Robert R.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Combustion efficiency was determined using natural gas fuel over a range of injection temperatures ...

Effect of increased fuel temperature on emissions of oxides of nitrogen from a gas turbine combustor burning ASTM jet-A fuel

Marchionna, N. R.

January 1974

An annular gas turbine combustor was tested with heated ASTM Jet-A fuel to determine the effect of i...

Effects of fuel nozzle design on performance of an experimental annular combustor using natural gas fuel

Wear, J. D.
Schultz, D. F.

November 1972

Tests of various fuel nozzles were conducted with natural gas fuel in a full-annulus combustor. The ...

Combustor technology for future aircraft

Tacina, Robert R.

January 1990

The continuing improvement of aircraft gas turbine engine operating efficiencies involves increases ...

Effect of increased fuel temperature on emissions of oxides of nitrogen from a gas turbine combustor burning natural gas

Marchionna, N. R.

December 1973

An annular gas turbine combustor was tested with heated natural gas fuel to determine the effect of ...

Development of a short-length turbojet combustor Summary report, 3 Jun. 1965 - 18 Apr. 1967

Kitts, D. L.

March 1968

Performance tests of short length, gas turbine combustors with atomized or vaporized fuel injectio

Effects of prevaporized fuel on exhaust emissions of an experimental gas turbine combustor

Ingebo, R. D.
Norgren, C. T.

January 1973

Effects of fuel vaporization on the exhaust emission levels of oxides of nitrogen (NOX), carbon mono...

Broad specification fuels combustion technology program

Dodds, W. J.
Ekstedt, E. E.

January 1984

Design and development efforts to evolve promising aircraft gas turbine combustor configurations for...

Performance of a short modular turbojet combustor segment using ASTM-A1 fuel [electronic resource] /

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

A 27-inch (68.6-cm) long rectangular combustor segment consisting of an array of 48 combustor module...

High-Pressure Combustion Testing Reveals Promise of Low-Emission Combustors for Advanced Subsonic Gas Turbines

Lyons, Valerie J.

March 1997

NASA Lewis Research Center's new, world-class, 60-atm combustor research facility, the Advanced Subs...

Research Data Acquired in World-Class, 60-atm Subsonic Combustion Rig

Lee, Chi-Ming
Wey, Changlie

April 1999

NASA Lewis Research Center's new, world-class, 60-atmosphere (atm) combustor research facility, the ...

Evaluation of an experimental short-length annular combustor: One-side-entry dilution airflow concept

Biaglow, J. A.
Humenik, F. M.

March 1973

A test program was conducted to evaluate an experimental short-length annular combustor that uses a ...