Afterburner

About: Afterburner is a research topic. Over the lifetime, 811 publications have been published within this topic receiving 5944 citations.

SOFC and gas turbine power systems—Evaluation of configurations for CO2 capture

Abstract: Publisher Summary This chapter highlights that pressurized solid oxide fuel cells (SOFC) integrated in a gas turbine cycle is a promising power generation concept The benefit of such combined systems is the potential for high electrical efficiency at small scale By including an afterburner for the fuel cell, the remaining fuel in the anode exit gas is fully converted to water and CO2 while the anode and cathode streams from the fuel cell are kept separated This enables the CO2 capture from an exhaust stream consisting of only CO2 and water This chapter evaluates, three afterburner technologies based on different membrane conductors from the perspective of thermodynamic cycle analysis and materials technology The total SOFC and gas turbine system with the different afterburners has been modeled in a general purpose flow sheet simulator, and mass and energy balances have been calculated The electrical efficiency has been determined and compared for each of the three afterburners The potential of the three technologies for future use as afterburners is evaluated

Gas turbine engine afterburner

Abstract: An afterburner 20 for a gas turbine engine 10 has a fuel spray ring 24a for injecting fuel into the afterburner, a flameholder gutter 34a for stabilizing combustion of a fuel-air mixture flowing through the afterburner, and an ignitor 35 for initiating combustion and includes an enclosure 50 attached to the gutter. The enclosure has radially inner and outer walls 52, 54 and circumferentially spaced apart webs 60, 62 extending between the walls to define a radially and circumferentially bounded chamber 64. Each web has a forward opening 72 and an aft opening 74 so that a portion of the spray ring and a portion of the gutter are embraced by the enclosure. The enclosure is ideally circumferentially aligned with the ignitor and regulates the fuel-air ratio within and in the vicinity of the chamber to ensure reliable lighting of the afterburner and flawless advancement to full afterburning operation.

Performance seeking control: Program overview and future directions

Abstract: A flight test evaluation of the performance-seeking control (PSC) algorithm on the NASA F-15 highly integrated digital electronic control research aircraft was conducted for single-engine operation at subsonic and supersonic speeds. The model-based PSC system was developed with three optimization modes: minimum fuel flow at constant thrust, minimum turbine temperature at constant thrust, and maximum thrust at maximum dry and full afterburner throttle settings. Subsonic and supersonic flight testing were conducted at the NASA Dryden Flight Research Facility covering the three PSC optimization modes and over the full throttle range. Flight results show substantial benefits. In the maximum thrust mode, thrust increased up to 15 percent at subsonic and 10 percent at supersonic flight conditions. The minimum fan turbine inlet temperature mode reduced temperatures by more than 100 F at high altitudes. The minimum fuel flow mode results decreased fuel consumption up to 2 percent in the subsonic regime and almost 10 percent supersonically. These results demonstrate that PSC technology can benefit the next generation of fighter or transport aircraft. NASA Dryden is developing an adaptive aircraft performance technology system that is measurement based and uses feedback to ensure optimality. This program will address the technical weaknesses identified in the PSC program and will increase performance gains.