Author: Nicholas R. MarchionnaPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
Book Description
Turbojet Combustor Performance with Natural Gas Fuel
Author: Nicholas R. MarchionnaPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
Book Description
Performance of a Turbojet Combustor Using Natural Gas Fuel Heated to 12000 F (922 K)
Author: James S. FearPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 28
Book Description
Combustion efficiency was determined using natural gas fuel over a range of injection temperatures from ambient to 1200' F (922 K). The combustor was comprised of three U-gutter flameholders mounted downstream of a trumpet-shaped diffuser in a rectangulai housing. A simple film-cooled liner was used. Tests were conducted at ambient pressure over a range of fuel-air ratios and combustor reference velocities. Increases in efficiency of more than 40 percentage points were achieved at the higher fuel temperatures. The results are applicable to natural gas afterburner design and to the design of advanced low-pressure-loss primary combustors.
Turbojet Combustor Performance with Natural Gas Fuel
Author: Nicholas R. MarchionnaPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 33
Book Description
Experimental Performance of a Modular Turbojet Combustor Burning Natural Gas Fuel
Author: Nicholas R. MarchionnaPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 38
Book Description
Performance of a Turbojet Combustor Using Natural Gas Fuel Heated to 1200 Degrees F (922 K)
Author: James S. FearPerformance of a Turbojet Combustor Using Natural Gas Fuel Heated to 1200° F (922 K)
Author: James S. FearPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 19
Book Description
Combustion efficiency was determined using natural gas fuel over a range of injection temperatures from ambient to 1200' F (922 K). The combustor was comprised of three U-gutter flameholders mounted downstream of a trumpet-shaped diffuser in a rectangulai housing. A simple film-cooled liner was used. Tests were conducted at ambient pressure over a range of fuel-air ratios and combustor reference velocities. Increases in efficiency of more than 40 percentage points were achieved at the higher fuel temperatures. The results are applicable to natural gas afterburner design and to the design of advanced low-pressure-loss primary combustors.
Performance of a Turbojet Combustor Using Natural Gas Fuel Heated to 12000 F (922 K)
Author: James S. FearPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 0
Book Description
Parametric Performance of a Turbojet Engine Combustor Using Jet A and A Diesel Fuel
Author: Helmut F. ButzePublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 50
Book Description
Gas Turbine Performance
Author: Philip P. WalshPublisher: John Wiley & Sons
ISBN: 140515103X
Category : Technology & Engineering
Languages : en
Pages : 664
Book Description
A significant addition to the literature on gas turbine technology, the second edition of Gas Turbine Performance is a lengthy text covering product advances and technological developments. Including extensive figures, charts, tables and formulae, this book will interest everyone concerned with gas turbine technology, whether they are designers, marketing staff or users.
Turbojet Combustor Performance with Injection of Hydrogen Peroxide for Thrust Augmentation
Author: Allen J. MetzlerPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 42
Book Description