Afterburning chamber of a gas turbine engine

 

Afterburning chamber of a gas turbine engine includes sequentially located along the gas flow path of the engine Saturninus channel and front-line unit comprising a V-shaped flame stabilizer, inside of which is placed the burner, which pass through holes in the top of the stabilizer is connected with the hollow intakes associated with nozzles and piping for supplying fuel. In the inside of the burner series gas tract are fuel-gas and gas radial swirlers with vanes having opposite spin. Each body of the burner with the input side of the stream is connected to a cylindrical thrust and floating bushings. The internal cavity of the floating sleeve is in contact with the outer surface of the fuel injector, and on the other side of the exit nozzles of the swirler body of the burner is connected with the inner cavity of the V-shaped stabilizer. The outlet nozzles of the gas swirl the conical wall is connected to a hollow cylindrical inner shell. On the outer surface of the body of the burner is a cylindrical flange with rachesky hollow inner shell and attached to the rear end of the flange outer shell with longitudinal ribs on the inner surface, contact on the outer surface of the cylindrical inner shell. The front face of the flange of the body of the burner is connected with a hollow intake, curved in the direction of gas flow, the inlet cross section which is perpendicular to the gas flow duct and arranged from the smallest bore securinega channel at a distance determined by the declared value. The invention allows for the optimum combination of values of hydraulic losses, high combustion and reliable operation of the afterburner. 3 Il.

The invention relates to the field of aircraft engine industry, in particular to the front-line devices afterburner combustion chambers.

Known front of the device containing the diffuser, Saturninus ring extending channel, the mixing system comprising a manifold with injectors, stabilizers, flame and heating pipe (see the book D. C. Cronin. "The construction and design of aircraft gas turbine engines". M. : Mashinostroenie, 1989, S. 444). In this type of afterburning chambers at the optimum combination of values of hydraulic losses, overall dimensions, mass and minimalist guest is ficient air excess equal to 1.1.

The closest in technical essence to the present invention is the device described the book D. C. Hronika "Construction and design of aircraft gas turbine engines". M.: Mashinostroenie, 1989, page 457...458. The known device comprises sequentially located on the air-gas flow path of the engine Saturninus channel formed by the inner surface of the housing securinega channel and the outer surface of the Central body, the front device that includes a housing with an outer wall, a V-shaped annular flame stabilizer, inside of which is placed the burner, which pass through holes in the top of the stabilizer is connected with the hollow intakes associated with nozzles and piping for supplying fuel. The inside of the stabilizer burner device in the known device to ensure the stable operation of afterburners and simultaneously to improve the combustion in the chamber.

However, the use of burners located inside of the stabilizer to vaporize liquid fuel, as a rule, leads to coking of fuel, clogging of the feed holes of the carbureted mixture in the zone of the CID is iunie the optimal combination of reliable operation of the afterburner, values of hydraulic losses, dimensions, mass, the minimum length of the combustion zone and ensure a high combustion in the afterburner in the whole operational range of the engine.

This technical result is achieved by the fact that the afterburning chamber of a gas turbine engine containing sequentially located along the gas flow path of the engine Saturninus channel formed by the inner surface of the housing securinega channel and the outer surface of the Central body, and front-line device that includes a housing with an outer wall, a V-shaped annular flame stabilizer, inside of which is placed the burner, which pass through holes in the top of the stabilizer is connected with the hollow intakes associated with nozzles and piping for supplying fuel, with each burner device comprises a hollow cylindrical body, in the walls of which consistently on the tract are topriority and gas radial swirlers with vanes having opposite spin, interscapular channels and output nozzles, each body of the burner with input is tulki contact with the outer surface of the fuel injector, on the other hand, the exit nozzles of the swirler body of the burner is connected with the inner cavity of the V-shaped stabilizer, a gas outlet nozzles swirl the conical wall is connected to a hollow cylindrical inner shell, in addition, on the outer surface of the body of the burner is a cylindrical flange with evenly spaced apertures around the circumference connected with the cavity formed by the cylindrical inner shell and attached to the rear end of the flange of the cylindrical outer shell with longitudinal ribs on the inner surface contacting the outer surface of the cylindrical inner shell, the front face of the flange of the body of the burner is connected with a hollow intake, curved in the direction of gas flow, the inlet cross section which is perpendicular to the gas flow duct and arranged from the smallest bore securinega channel on the distance determined from the relation FminuteschannelFminutes 1+Fminutes 2+F3where Fminuteschannelring the smallest flow cross section of the outer wall of the front of the device and the casing of the V-shaped annular stabilizer; Fminutes 2ring the smallest flow area of a flow path between the housing V-shaped annular stabilizer and a wall of the Central body; F3- the total area of the flow areas of the channels in the buildings toplivopitanija swirl, gas swirl and holes between the outer and inner cylindrical shells all burners.

The performance of each burner in the form of a hollow cylindrical body, the walls of which consistently on the tract are topriority and gas swirler with blades having opposite spin, in this case the centrifugal atomizer atomizes the fuel, forming a cone spray pattern with a twist in the same direction as topriority swirl cone spray fuel intersects with the flow of gas emerging from the interscapular channels toplivopitanija swirl, slurp it, gets an additional spin and, jumping up from the edges of the output nozzle, forms a cone spray toplinarstvo mixture. Simultaneously, the gas discharged from interscapular channels gas swirl, form your cone spray pattern, but with a smaller angle than the angle at the cone spray pattern toplinarstvo mixture. Next cone RASPA border rotating in opposite directions of the gas streams and toplinarstvo mixture, emerging from the interscapular channels in the output nozzle of swirlers, allow spray toplinarstvo mixture in carburising zone reverse currents output from the cylindrical outer and inner shells and, in addition, the presence of through-holes in the cylindrical flange of the body of the burner connected to the cavity formed by the cylindrical hollow inner shell and attached to the rear end of the flange of the cylindrical outer shell with longitudinal ribs on the inner surface contacting the outer surface of the cylindrical inner shell, also allows you to generate on the output edges of cylindrical shells additional disruption of the flow area of the reverse currents and thereby to enhance the mixing of the cold streams of gas emerging from the burner device carburising mixture, which then gets into the zone of circulation V-shaped annular stabilizer, forming an area of the reverse currents of the entire burner afterburner, and thereby to obtain a small length of the combustion of fuel with high combustion in the entire operating range of the coefficient of excess air.

The connection of the front torus flow of gas, and orthogonal input cross-section, which is located from the smallest bore securinega channel on the distance determined from the relation FminuteschannelFminutes 1+Fminutes 2+F3allows you to provide a minimum hydraulic losses tract and the optimum pressure drop across the burner device, and hence the optimal gas flow through each burner device.

The invention is illustrated by drawings.

In Fig. 1 shows a longitudinal section of the afterburner of a gas turbine engine.

In Fig. 2 shows a longitudinal section of a burner with explaining his design cross sections.

In Fig. 3 shows a longitudinal section of a centrifugal atomizer with explaining the design cross section.

Afterburner chamber 1 gas turbine engine 2 contains Saturninus channel 3 with case 4, the Central body 5, the front device 6, the front housing of the device 7, a V-shaped annular stabilizer 8, the burner 9, the hollow intakes 10 with an input section 11, the centrifugal nozzle 12 with tangentiality channels 13, pipelines for supplying fuel 14. Empty the 16 with blades 17, with interscapular channels 18 and outlet nozzles 19, the gas radial swirler 20 with blades 21, interscapular channels 22 and output nozzles 23, the cylindrical floating sleeve 24 and a thrust bearing 25, the conical wall 26, a hollow cylindrical inner shell 27, a cylindrical flange 28 with evenly spaced around the circumference of the through-hole 29, a cylindrical outer shell 30 with longitudinal ribs 31, the annular channel 32 between the cylindrical outer and inner shells. The drawing also depicts the turbine 33 with the rear pillar 34 of the gas turbine engine.

Afterburning chamber of the gas turbine engine operates as follows.

When the engine is in the afterburning mode gas from the turbine 33 is supplied by saturnina channel 3, the output of which is made in the form of a cone, where the reduced flow rate and equalized ripple. Then the gas enters at the front of the device 6, passes through it and simultaneously fed to the inputs of hollow intakes 10, bent in the direction of gas flow, with the input sections 11 arranged from smallest bore securinega channel 3 on the distance determined from the relation Fminuteska is e housing 15 of burners 9. At the same time the fuel pipeline 14 is fed into the centrifugal nozzle 12, where tangentiality channels 13 rasplivaetsa, forming a cone spray fuel spin in the same direction as the gas discharged from interscapular channels 18 toplivopitanija swirl with 16 blades 17. Cone spray fuel intersects with the stream of gas leaving toplivopitanija swirl 16, captured them, gets more spin and, jumping up from the edges of the output nozzle 19, forms a cone spray toplinarstvo mixture. Simultaneously, the gas passing through the hollow cylindrical body 15 comes in interscapular channels 22 of the gas swirler 20 with blades 21, twisting the gas flow in the opposite direction of the spin flow toplevelitem swirler 16. The gas leaving the swirler 16, the output nozzles 22 form your cone spray pattern, but with a smaller angle than the cone angle of the spray toplinarstvo mixture. Next cone spray toplinarstvo gas mixture and overlap, and due to the impact of tangential stresses arising at the border rotating in opposite directions of the gas streams and toplinarstvo mixture emerging from the interscapular channels 18 and 22 in the output nozzle 19 and 23 of the swirler inner and outer shells 27 and 30. Simultaneously, the gas from the hollow intakes 10 passes through the through hole 29 in the cylindrical flange 28 of the housing of the burner 15, enters the cavity formed by the inner shell 27 and is attached to the rear end of the flange 28 of the cylindrical outer shell 30 with longitudinal ribs 31 on the inner surface contacting the outer surface of the cylindrical inner shell 27, where, after passing through the channels 32, generates on the output edges of cylindrical shells 27 and 30 additional disruption of the flow area of the reverse currents and thereby activates the mixing of the cold streams of gas emerging from the burner device carburising mixture, which then gets into the zone of circulation V-shaped annular stabilizer 8, forming an area of the reverse currents of the entire burner afterburner 1. The initial ignition of the fuel in the afterburner (start) is performed with the use of spark plugs, igniters, "fire lanes" (conventionally in the drawing not shown) or the high-temperature operating modes of the engine by the ignition afterburner fuel. At the termination of supply of afterburner fuel afterburning chamber off from work, and Diogo engine provides an optimal combination of values of hydraulic losses, dimensions, mass, the minimum length of the combustion zone while increasing combustion 5...7% and reliable operation of afterburners in the whole operational range of the engine.

Claims

Afterburning chamber of a gas turbine engine containing sequentially located along the gas flow path of the engine Saturninus channel formed by the inner surface of the housing securinega channel and the outer surface of the Central body, and front-line device that includes a housing with an outer wall, a V-shaped annular flame stabilizer, inside of which is placed the burner, which pass through holes in the top of the stabilizer is connected with the hollow intakes associated with nozzles and piping for supplying fuel, with each burner device comprises a hollow cylindrical body, the walls of which consistently on gas tract are topriority and gas radial swirler blades, having the opposite spin, interscapular channels and output nozzles, each body of the burner with the volt is ulki contact with the outer surface of the fuel injector, on the other hand, the exit nozzles of the swirler body of the burner is connected with the inner cavity of the V-shaped stabilizer, and the exit nozzle of the gas swirl the conical wall is connected to a hollow cylindrical inner shell, in addition, on the outer surface of the body of the burner is a cylindrical flange with evenly spaced apertures around the circumference connected with a cavity formed by a cylindrical hollow inner shell and attached to the rear end of the flange outer shell with longitudinal ribs on the inner surface contacting the outer surface of the cylindrical inner shell, the front face of the flange of the body of the burner is connected with a hollow intake, curved in the direction of gas flow, the inlet cross section which is perpendicular to the gas flow duct and arranged from the smallest bore securinega channel on the distance determined from the relation

Fminutes channelFminutes 1+Fminutes 2+F3

where Fminutes channelring the smallest orifice C is waiting outside wall of the front of the device and the casing of the V-shaped annular stabilizer;

Fminutes 2ring the smallest flow area of a flow path between the housing V-shaped annular stabilizer and a wall of the Central body;

F3- the total area of the flow areas of the channels in the housings of the fuel gas swirl gas swirl and holes between the outer and inner cylindrical shells all burners.

 

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