Topic
Afterburner
About: Afterburner is a research topic. Over the lifetime, 811 publications have been published within this topic receiving 5944 citations.
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Patent•
25 Apr 2018
TL;DR: In this article, an improved quality of control of the gas-turbine engine with an afterburner was provided by providing optimal conditions for ignition of the after-burner by expanding the area of stable ignition by implementing optimal programs for controlling the pressures ratio in given engine sections in transient and steady-state operating modes.
Abstract: FIELD: engines.SUBSTANCE: group of inventions relates to aircraft engineering. In the method for control of gas-turbine engine with afterburner in transient operating modes of the gas-turbine engine, a predetermined value of the pressures ratio in the predetermined engine sections is formed depending on the reduced rotor speed of the low pressure compressor and is adjusted depending on acceleration of the high pressure compressor rotor, and in the steady-state operating modes of the gas-turbine engine, the predetermined value of the pressures ratio in the predetermined engine sections is formed depending on the air temperature at the inlet to the engine. Control system of the gas-turbine engine with an afterburner is also described.EFFECT: technical result is improved quality of control of the gas-turbine engine with an afterburner by providing optimal conditions for ignition of the afterburner by expanding the area of stable ignition of the afterburner by implementing optimal programs for controlling the pressures ratio in given engine sections in transient and steady-state operating modes, and also due to a more precise limitation of the maximum permissible temperature of the gases in front of the turbine nozzle apparatus and increased completeness of fuel combustion.2 cl, 1 dwg
Patent•
07 Jan 2020
TL;DR: In this paper, an electrically-driven afterburner and an area-adjustable exhaust nozzle integrated structure is presented, which is applicable to aero-turbine engines.
Abstract: The invention relates to an electrically-driven afterburner and area-adjustable exhaust nozzle integrated structure and is applicable to aero-turbine engines. Lever execution mechanisms for controlling an area-adjustable exhaust nozzle are arranged at the front end of the afterburner; one end of each lever execution mechanism is connected with an execution connecting rod of an electric execution steering engine, and the other end is connected with an execution ring of the area-adjustable exhaust nozzle. The two electric execution steering engines are adopted, the opening area of the exhaust nozzle is controlled, and the requirement for area change of the exhaust nozzle during working of the afterburner is met. According to the structural scheme, adjustment of the overall structure of the engines is not involved, the movement fulcrum is fixed to the front-end flange surface of the afterburner, and the driving capability of the electric steering engines is magnified with the lever principle, so that the controllability of the adjustable exhaust nozzle is improved effectively; and the complex hydraulic control structure is cancelled, so that the control execution mechanism is simplified.
Patent•
20 Feb 2021
TL;DR: In this article, a hydraulic accumulator connected to the impeller by a first feed line and a return line at the outlet of the turbine, wherein valves allow fluid flowing from storage battery to flow into turbine, when the afterburner is actuated, and the possibility of reducing or stopping the flow of fluid medium under pressure stored in the accumulator, to the turbine for stopping the augmented power plant.
Abstract: FIELD: aviation.SUBSTANCE: invention relates to propulsion plants of aircraft. Propulsion system (110) of aircraft (100) includes fan, main power plant, afterburner, control device, hydraulic coupling assembly (160) and hydraulic circuit. Hydraulic circuit is configured to adjust hydraulic coupling assembly (160). Hydraulic clutch assembly (160) has a hydraulic accumulator connected to the impeller by a first feed line and a return line at the outlet of the turbine, wherein valves allow fluid flowing from storage battery to flow into turbine, when the afterburner is actuated, and the possibility of reducing or stopping the flow of fluid medium under pressure stored in the accumulator, to the turbine for stopping the augmented power plant.EFFECT: higher efficiency of the engine.12 cl, 20 dwg
Patent•
28 Feb 2020
TL;DR: In this paper, an afterburner and free nozzle coupling control method for a small turbojet engine is presented, which adjusts and determines the control law of after-burner regulation according to the actual working state of the engine in the testing stage.
Abstract: The invention relates to the field of afterburner and free nozzle coupling control of small turbojet engines, and discloses an afterburner and free nozzle coupling control method for a small turbojetengine. The purpose is to adjust and determine the control law of afterburner and free nozzle regulation according to the actual working state of the engine in the testing stage, determine the optimummatching parameters of an afterburner and a free nozzle in a self-compensation way and realize the coordinative and cooperative work of the afterburner and the free nozzle of the small turbojet engine in an afterburner and free nozzle coupling control way. The afterburner and the free nozzle of the small turbojet engine can be under automatic coupling control, so that an afterburner fuel regulation system and an actuation system are automatically matched for regulation, and accordingly the actual optimal performance operating point of the small turbojet engine is quickly determined.
01 Apr 2014
TL;DR: The afterburner system is supplied the gas O2 and gas CH4 to reduce the harmful exhaust gas in the combustion chamber of the liquid rocket engine for KSLV-II in NARO Space Center as mentioned in this paper.
Abstract: Combustion Chamber Test Facility (CCTF) is under construction to test the combustion chamber and the gas generator of liquid rocket engine for KSLV-II in NARO Space Center. The CCTF includes the afterburner which is combustion system to reduced the harmful products of gas generator. The afterburner system is supplied the gas O2 and gas CH4 to reduced the harmful exhaust gas. The CCTF Afterburner system is simulated and analysed by AMESim program through the all of gas supply system components. This study is performed to determine the pipes, orifice diameter, and gas supply conditions according to the total gas consumption from analysis of gas supply system.