Showing papers on "Afterburner published in 1991"

Film cooled combustor liner for gas turbine

Abstract: A gas turbine engine combustor is provided, having a single wall sheet metal liner which is generally annular in shape which may be corrugated and a multi-hole film cooling means which includes at least one pattern of a great many small closely spaced sharply downstream angled film cooling holes [80] disposed essentially along portion of the liner to be cooled. Another embodiment provides a corrugated aircraft engine afterburner sheet metal liner having at least one pattern of great many small closely spaced sharply downstream angled film cooling holes disposed essentially along the entire surface of the liner.

Treatment of exhaust gas - involves afterburner and catalyst together with flame barrier to impede gas flow

Abstract: The arrangement is for handling the exhaust gas of an IC engine. It comprises a catalyst (9) and an afterburner (8) arranged in front of it. The catalyst has a carrier body (10) for the catalytic layer exposed to through flow and is surrounded by a housing (18), upstream of which is provided the combustion chamber (12) of the afterburner, also surrounded by the housing, with a flame barrier (16) to prevent the free flow of gas. USE/ADVANTAGE - Exhaust system which reduces harmful emissions during the IC engine warm-up phase.

Power generating method by co reheat gas turbine combined cycle

Abstract: PURPOSE:To prevent generation of air pollution substances such as MOx, SOx, etc., by generating power through a CO reheat gas turbine in which carbon dioxide gas is produced by using oxygen gas as a combustion oxidizing agent to perform combustion of carbon monoxide gas and circulated as working fluid. CONSTITUTION:In a CO reheat gas turbine 1, in a combustor 4, combustion of carbon monoxide gas CO is performed by oxygen gas O2 to produce carbon dioxide gas CO2, and in a high pressure turbing 5, power is generated with the above described CO2 gas serving as working fluid, while in an intermediate pressure turbine 6, power is generated with the CO2 gas, discharged from the turbine 5, serving as working fluid. In an afterburner 7, the CO2 gas, discharged from the turbine 6, is mixed to burn the CO gas by O2 gas with the CO2 gas produced, and in a low pressure turbine 8, power is generated with the CO2 gas from the afterburner 7 serving as working fluid. That is, by using not air but O2 gas as a combustion oxidizing agent while CO in place of fossil fuel, respectively, generation of NOx and SOx is prevented.

Control of combustion-induced instabilities

Abstract: An active control for controlling combustion induced instabilities in a combustion chamber (17) e.g. of a turbine with combustor fuel nozzles for providing fuel in the combustion chamber is provided. The active control includes a pressure transducer (43) for measuring pressure fluctuations in the combustion chamber and a servovalve (53) for modulating the amount of fuel supplied to the fuel nozzles. A phase shifter (47) coupled between the pressure transducer and the servovalve is adjusted so that the amount of fuel supplied for combustion is reduced during pressure peaks. This results in a sufficient phase shift between the fuel flow and unsteady pressure fluctuations. In a second embodiment a similar arrangement is also used to control instabilities in an afterburner (23) by modulating fuel flow to the spray bars (27) as described above.

Gas turbine engine multi-hole film cooled combustor liner

Abstract: A gas turbine engine combustor is provided, having a single wall sheet metal liner which is generally annular in shape which may be corrugated and a multi-hole film cooling means which includes at least one pattern of a great many small closely spaced sharply downstream angled film cooling holes disposed essentially along portion of the liner to be cooled. Another embodiment provides a corrugated aircraft engine afterburner sheet metal liner having at least one pattern of great many small closely spaced sharply downstream angled film cooling holes disposed essentially along the entire surface of the liner.

Weak Extinction Limits of Large Scale Flameholders

Abstract: Weak extinction data obtained from an experimental apparatus designed to simulate the characteristics of practical afterburner combustion systems are presented. The apparatus supplies mixtures of varied composition (equivalence ratio and degree of vitiation), temperature and velocity to Vee-gutter flame holders of various widths and shapes similar to those found in jet engine systems. The fuel employed is a liquid hydrocarbon whose chemical composition and physical properties correspond to those of aviation kerosine, JP5. An equation for predicting weak extinction limits which accounts for upstream vitiation and the chemical characteristics of the fuel is derived from stirred reactor theory. The correlation between the predictions and experimental results indicates that the stirred reactor approach can provide a framework for predicting the lean blowout limits of practical flameholders over wide ranges of engine operating conditions.Copyright © 1991 by ASME

Adjustable nozzle for hypersonic engine combustion chamber

Abstract: In a ram jet combustion chamber having fuel injectors 34 and an exhaust nozzle 7, the nozzle throat cross-section (between the widest part of a displacement body 15 and an outer wall 10 increases along with increase in combustion space length as the body 15 axially slid able on a support pipe 18 is moved outwards, and conversely, both parameters decrease as the body (15) is moved inwards. This interdependence results in highly effective ram-jet operation. In other embodiments, air may be delivered to the ram jet combustion chamber by a double pipe (figs 2 to 5) or may serve as a combined ram-jet combustion chamber and afterburner chamber of turbo engine (figs 6 and 7) which may have a bypass arrangement.

Feasibility study of air-breathing turboengines for horizontal takeoff and landing space planes

Abstract: Various concepts of air-breathing engines (ABEs) that could be used for a horizontal take-off and landing SSTO vehicle are investigated. The performances (with respect to thrust and the specific fuel consumption) of turboengines based on various technologies, including a turbojet with and without afterburner (TJ), turboramjet, and air-turbo-ram jet engines are compared. The mission capabilities of these ABEs for SSTO and TSTO vehicles is examined in terms of the ratio of the effective remaining weight (i.e., the weight on the orbit) to the take-off gross weight, using two-dimensional flight analysis. It was found that the dry TJ with the turbine inlet temperature 2000 C is one of the most promising candidates for the propulsion system of the SSTO vehicle, because of its small weight and high specific impulse. 6 refs.

Thrust augmented bypass gas turbine engine

Abstract: Buckling loads across an afterburner combustion liner 52 are reduced by means for creating pressure losses in the bypass flow 96 to a plenum 54 surrounding the afterburner liner 52, thereby reducing differential pressure acting across the liner Preferably, the bypass airflow is accelerated to a velocity greater than Mach 1 and is then decelerated to a velocity less than Mach 1 for incurring shock waves for generating the pressure losses The necessary air flow may be produced by a separate guide 68 (& Fig 7) (70) (Fig 5) or a modification (12) (Fig 4) of an engine casing wall A mixing device 62 (eg of the lobed variety) may be provided for mixing a portion 86 of the bypass flow 46 with core engine gas flow 38 upstream of the afterburner fuel injectors 58