Patent
Shortened afterburner construction for turbine engine
TLDR
An afterburner construction for a turbine engine such as a turbofan engine is foreshortened by using a construction which utilizes swirl flow phenomena to rapidly mix the engine products of combustion and coolant flow, such as fan air, while maintaining engine performance and structural part integrity as mentioned in this paper.Abstract:
An afterburner construction for a turbine engine, such as a turbofan engine, which is foreshortened by using a construction which utilizes swirl flow phenomena to rapidly mix the engine products of combustion and coolant flow, such as fan air, and/or to rapidly accomplish the afterburning combustion process in the afterburner, while maintaining engine performance and structural part integrity.read more
Citations
More filters
Patent
Compact swirl augmented afterburners for gas turbine engines
Stephen N. Schmotolocha,Donald H. Morris,Robert J. Pederson,Raymond B. Edelman,Calvin Q. Morrison +4 more
TL;DR: The swirl generator as discussed by the authors converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced, and the generator is configured in a backward-flowing manner that carries heat and combustion byproducts upstream to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers.
Patent
Gas turbine engine ignition flameholder with internal impingement cooling
TL;DR: In this paper, a cooled ignition flameholder assembly includes a first heat shield having first and second spaced apart chambers, and a hollow baffle is disposed inside the second chamber, which includes an inlet for receiving cooling air which is discharged through a plurality of outlet holes for impingement cooling the heat shields.
Patent
Bypass duct of a turbofan engine
TL;DR: In this article, the fairing element with a specific outer contour is integrated into the downstream guide vane assembly, which results in lower pressure losses and reduced fuel consumption as well as reduced pressure effect on the fan and, consequently, increased operating stability of the fan.
Patent
Single-stage hypersonic vehicle featuring advanced swirl combustion
TL;DR: In this article, a single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system, and the low-s speed propulsion system is used to accelerate the single stage vehicle to a threshold velocity, after which the high speed propulsion systems then takes over.
Patent
Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance
Stephen N. Schmotolocha,Robert J. Pederson,Calvin Q. Morrison,Raymond B. Edelman,Donald H. Morris +4 more
TL;DR: A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant is described in this article, where a toroidal outer recirculation zone and an inner central recirculating zone are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers and stabilizes flame propagation and accelerates combustion throughout the entire combustor.
References
More filters
Patent
Ducted fan-jet engine
TL;DR: In this article, a ducted fan-jet power plant in which a part of the bypass airflow supplied by the low-pressure compressor is conducted through hollow turbine discharge guide blades, open at their trailing edges, for the purpose of mixing the bypass flow and the main flow of the power plant within the area of the turbine discharge blade.
Patent
Combustion chamber for a gas turbine engine
TL;DR: In this paper, a gas turbine engine combustion equipment comprises outer and inner casings enclosing an annular flame tube 20 having inlet guide vanes 23 mounted in the upstream end thereof to direct air from the engine compressor towards a combustion zone 24.