Afterburning fuel

 

(57) Abstract:

The invention concerns a device afterburning of fuel, using the stabilizer flame carburising type with optimized cooling system. This flame stabilizer includes a housing (34), which runs in the radial direction in the primary flow of gases and is a structure in the form of a V-shaped dihedral angle, containing two side plates (35, 36) having one common unifying their rounded edge (37), the ventilation tube (38) located between two side plates (35, 36), and at least one fuel conduit (44, 45), located at the edge of the ventilation tube (38). Vent pipe (38) has a generally triangular cross-section and includes at its rear on the flow surface of the groove (42) where the fuel pipes (44, 45). Vent pipe (38) also contains holes (41, 46), designed for intensive cooling of the side plates (35, 36) of the structure in the form of a dihedral angle and fuel lines (44, 45). This embodiment of the device afterburning of fuel leads to improved cooling. 2 C.p. f-crystals, 6 ill.

Currently, WPI is bugcontrol turbojet engine, containing an outer annular casing, almost with the axis of rotation, the exhaust casing, is positioned inside the outer casing and containing an outer annular wall and an inner annular wall, each of which has the same axis of rotation as the outer casing, and bounding with him the first pass, intended for the flow of secondary air, and the outer annular wall and the inner annular wall of the limit between a second pass, intended for the flow of gaseous products of combustion, and the afterburning device also includes an annular wall of the combustion chamber with the own axis of rotation, and the external casing, and positioned inside the outer casing, being remote from him at a certain distance, thereby to form a passage for cooling air, and limiting the secondary combustion chamber to flow behind the said first and second passages, brackets stabilizers flame, passing in planes radial to the axis of rotation, at least within the second passage, each of which is made in the form of a dihedral angle, limited by two external plates having a common edge connections and forming the days downstream part of the combustion chamber relative to the axial direction of flow of the gaseous products of combustion, each flame stabilizer further comprises a ventilation tube with many holes, intended for cooling the outer plates by means of the cooling air taken in the first passage, and at least one radially located the fuel supply pipes with holes injection of fuel.

Ventilation tube described in this document, has a round cross section, is located in the immediate vicinity of the edge or vertex of the dihedral angle and contains openings intended for cooling of the wings of this dihedral angle. Special screen that prevents thermal radiation and having a semicircular cross section, is located downstream behind the fuel supply between the rear downstream edges of the dihedral angle and lateral axial slits intended for the flow of the mixture of fuel with air in the secondary combustion chamber. Hole injection of the fuel supply are holes located in a strictly radial planes, directed towards the inner walls mentioned dihedral angle. The flame stabilizer of this type are called carburising.

Bid, medium, small is broken off designs in the form of a dihedral angle and containing the ventilation tube, designed for cooling mentioned dihedral angle.

In this last mentioned source of the flame stabilizer does not contain any of the fuel supply, no screen, preventing thermal radiation. In this case, the fuel is injected at the flow front from these stabilizers flame with pipe fuel supply, located on the sides of the connecting brackets, which are located alternately between the stabilizers flame. Injected into the combustion chamber, the fuel flow on the external walls of the flame stabilizers. Cross section of the ventilation tube in this case has a value exceeding the value of the cross-section of the cylindrical tube, referred to in the source FR 2709342 that provides the best conditions for the cooling of the walls mentioned dihedral angle. However, in this case, the channels of the fuel is exposed to heat flow coming from the gaseous products of combustion that can lead to disruption of the normal functioning of the channels due to the danger of coking and steam tube ("vapor-lock").

The objective of the invention is to create a device afterburners the above-mentioned technical solutions.

The problem posed in the present invention, is achieved by optimizing the device aerodynamic cooling of each of the stabilizer flame.

To achieve its tasks in accordance with the invention, the ventilation tube has a generally triangular cross-section and includes two side surfaces are parallel outer plates, and the back flow surface in the form of radial troughs, in which is located the fuel pipe, and many additional holes directed towards this fuel line, made in the wall of the trench in order to provide ventilation and cooling of the fuel pipeline, which provides the injection of fuel in the direction of the flow.

Due to the proposed design flow section of the ventilation tube in this case is larger than the round bore of the vent tube, described in French patent FR 2709342. Due to this, the cooling air is increased and the outer plate design in the form of a dihedral angle cooled blows streams of air flowing from the holes formed on the sides of the wire in all ranges of operation of this turbojet engine, what prevents the danger of coking and formation of steam tubes, and also contributes to thermal stability of the fuel pipe and the so-called dry mode, i.e. in the absence of the functioning of the after-burning chamber or afterburner. The location of the holes and the shape of the cross section of the ventilation tube of the stabilizer flame, best adapted to ensure proper ventilation of the wall structure in the form of a dihedral angle and the fuel line.

In a preferred implementation of the present invention, the fuel pipe is equipped with fuel injectors aeromechanical type. This solution allows you to provide a satisfactory quality of fuel atomization and control the width of the cone distribution of the droplets of fuel in order to eliminate any risk of collision with the external plates of the aforementioned structure in the form of a dihedral angle of this system afterburning.

Other advantages and features of the invention will be better understood from the following description of the example of its practical implementation, where references are given in primogenitor flame in accordance with the current level of technology in this field;

Fig. 2 is a schematic view in section decarburising of the flame stabilizer in accordance with the current level of technology in this field;

Fig. 3 is a schematic view in axial section of half part of the turbojet engine, containing the afterburning of fuel in accordance with the invention;

Fig. 4 is a schematic view in section along the line IV-IV shown in Fig. 3;

Fig. 5 is a partial schematic perspective view of the device of the flame stabilizer in accordance with the invention;

Fig. 6 is a schematic perspective view of the fuel line.

In Fig. 1 presents a schematic view in section of the stabilizer flame carburising type, similar to the flame stabilizer described in the patent application published under the number FR 2709342. The flame stabilizer is located radially in the flow of hot gases moving in the channel of this turbojet engine in the direction shown by the arrow G. the stabilizer flame contains sheet metal, bent in the form of V-shaped degranulate downstream portion of the flame stabilizer, relative to the direction of flow of hot gases G, and further comprises a ventilation tube 5, which made many through holes, which is circular in cross section and which is located between the side plates 2 and 3 designs in the form of a dihedral angle near the rounded edge or the top 4 this durannie, the fuel pipe 6 located downstream behind the said vent tube 5, and the screen counter-radiation 7, which has a concave surface facing in the direction of the flow of gases, and which connects the rear flow edges 8 and 9 of the side plates 2 and 3 mentioned dihedral design, forming side slits 10 and 11 designed to drain formed of the mixture of fuel with air.

In this case vent tube 5 contains holes 12, intended for blowing clean air coming from the fan of this turbojet engine in the direction of the mentioned plates 2 and 3 and in the direction of the rounded edges 4.

Holes 13 of the fuel pipe 6 inject a certain amount of fuel 14 in the direction of the said lateral slots 10 and 11.

In Fig. 2 presents schematizes the WMD in the application for patent in France, published under the number 2696502.

This stabilizer flame 1' is also made in the form of a design in the form of a dihedral angle having two side plates 2' and 3' connected to a rounded edge or a vertex of this angle 4', oriented in the direction against the flow relative to the axial direction G of the flow of hot gases. Located in the axial direction of the vent pipe 5' is held between the side plates 2' and 3'. This vent pipe 5' has a generally triangular cross-section, the sides 15 and 16 which are arranged in parallel and next to the said side plates 2' and 3' and contain openings 12, which provide the injection of clean air taken in the channel of the secondary air coming from a fan of this turbojet engine in the head part of the ventilation tube 5', in the direction of the inner surfaces mentioned dihedral design. Back on the thread surface of the ventilation tube 5' is made concave and contains 18 holes, designed to supply clean air to flow in the secondary combustion chamber 19.

Turbofan engine and its camera dogboy body of rotation with the axis of rotation 21, the casing of lead 22 of the gaseous products of combustion, through which pass the guide vanes of this turbojet engine and where the movement of the gas stream in the direction shown by the arrow G, and the afterburner fuel 23, located on the flow behind the casing of lead 22 of the gaseous combustion products.

Casing discharge or exhaust 22 is located inside the outer casing 20 and limits with him the first passage 24, in which the flow of secondary air's coming from a fan of this turbojet engine.

Casing discharge or exhaust 22 formed in the outer annular wall 25 with the axis of symmetry 21. This case leads 22, the outer wall 25 and inner wall 26 are connected by means of radial connecting levers, not shown in the Appendix figures.

The outer wall 25 and inner wall 26 of the limit between the second passage 27 that is designed for the flow of flow of the gaseous combustion products.

The annular wall 28 of the afterburning fuel with the axis of symmetry 21, which is radially more distant from the axis 21 than the outer wall 26 of the afterburner fuel or afterburners 23.

The above-mentioned brackets stabilizers flame 30 which are inclined in the radial direction toward the combustion chamber 20, are located on the border of the casing discharge or exhaust 22 and the afterburner 23. Each bracket flame stabilizer 30 is held strictly in a radial plane containing the axis of symmetry 21 or passing through this axis.

Each bracket flame stabilizer 30 includes a head portion 31, which intersects the first passage 24, mentioned above, and which holds at its rear flow side of the annular afterburning combustion chamber 32 with the axis of symmetry 21 connected by means of the fuel pipe 33 with the fuel supply line 33a, and the main body 34, which is held inside the second passage 27 and which is the object of the present invention.

Thus, as can be seen in Fig. 4, 5 and 6, the main body 34 is made in the form of a dihedral angle having a V-shaped cross-section, and the top of this dihedral angle is oriented against the direction of flow of gases, and its branches are oriented along the flow G these hot gases. This design is in the form of a dihedral angle contains two outer plates 35 and 36 having a common joint is the main body 34. The vent tube 38 is open at its end remote from the axis of symmetry 21 in order to enable the selection of a certain amount of cooling air is R in the first passage 24, and is closed at its lower end. The vent tube contains along its entire length with a number of holes designed to remove selected air outside the tube 38.

Vent pipe 38 generally has a triangular cross-section and includes two side walls 39, 40, strictly parallel outer plates 35, 36, which are located at a short distance from these side walls in order to provide opportunity for intensive cooling of the outer plates 39, 40 of the air flowing out of the holes 41. Back on thread surface 42 of the ventilation tube, which is directed towards the inner part of the after-burning chamber or afterburner chamber 23 has a convex shape and contains a groove 43 of the U-shaped cross-section, in which there are two radial fuel pipe 44 and 45, powered by fuel. In the wall bounding the groove 42, the holes 46 through which the cooling air enters in the direction of the above-mentioned fuel lines 44 and 45.

Vent pipe 38 of the flame stabilizer 30 performs the function of the structural core and the supply channel a certain amount of air R, coming from a fan of this turbojet engine. The supply of clean air R is performed in the whole range of operation of this turbojet engine in order to prevent the danger of coking and the emergence of the steam tubes in the afterburning mode and dry mode operation.

The shape of the vent tube 38, and the location of the holes 41 and 46, is best adapted to provide thermal integrity of the fuel injector.

The device in accordance with the proposed invention allows also to provide thermal integrity of the wall structure in the form of a dihedral angle and the system is et to refuse the use of organs injection, installed in the primary stream, in the case of stabilizers, flame not carburising type, which provides a higher reliability of operation in the prevention of the danger of return fire. The proposed solution also allows the use of composite materials for the implementation of these designs in the form of a dihedral angle, which provides a definite advantage in weight referred to the design.

1. Afterburning of fuel that is designed to bypass turbofan engine and containing an outer annular casing (20) having an axis of rotation (21), casing discharge or exhaust (22) that is positioned inside the outer casing (20) and containing an outer annular wall (25) and the inner annular wall (26), each of which has the same axis of rotation or axis of symmetry, and the external casing (20), and bounding together with the external casing of the first passage (24) intended for the flow of secondary air, moreover, the outer annular wall (25) and the inner annular wall (26) limit between the second passage (27), designed for the flow of gaseous products of combustion, and this device daihani nasni casing (20), and inside the outer shell, which is separated from it by a certain distance so as to define a passage for cooling air, and limiting the secondary combustion chamber or afterburner chamber (23) in the flow behind the first (24) and second (27) passes, and the brackets stabilizers flame (30) are in radial planes with respect to the symmetry axis (21), at least within the second passage (27) and each of these brackets is a structure in the form of a dihedral angle, limited by two external plates (35, 36)connected between a common edge (37), and having a cross section U-shaped, the top of which is oriented in the direction against the flow of hot gases in relation to the General direction (G) flow of gaseous products of combustion, and each flame stabilizer (30) further comprises a ventilation tube (38) that contains many holes and designed for cooling the outer plates (35, 36) by means of the streams of the cooling air taken in the first passage (24), and cooling at least one radial fuel line (44, 45), with openings for the injection of fuel, different arnosti (39), (40), strictly parallel outer plates (35, 36), and back along the flow surface (42), which is a radial groove (43), in which is located the fuel pipe (44, 45), and many additional holes (46), oriented in the direction of the fuel pipe, made in the wall (42) of the gutter (43) in order to ensure adequate ventilation of the fuel pipeline, which provides the injection of fuel in the direction of flow of the flow of hot gases.

2. The device under item 1, characterized in that the fuel pipe (44, 45) equipped with fuel injectors aeromechanical type (46).

3. Device according to any one of paragraphs.1 and 2, characterized in that each of the stabilizers flame (30) contains two fuel pipe (44, 45).

 

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