RU2290565C1 - Fuel sprayer of combustion chamber of gas turbine engine - Google Patents

Abstract

FIELD: fuel sprayer for combustion chamber of gas turbine engine.

SUBSTANCE: fuel sprayer includes body with ducts and with unions of main and additional circuits for fuel supply to main and additional jets arranged in head of sprayer; mounting flange for securing sprayer to outer housing of combustion chamber, IN duct of main circuit dividing tube is arranged. Inside said tube there is duct of additional circuit. One end of dividing tube is mounted in head of sprayer by means of non-detachable joint relative to body. Other end of dividing tube is arranged inside body at outer side from mounting flange between unions of main and additional circuits and telescopically relative to duct of main circuit by means of cylindrical protrusion. Dividing tube engages by its one end with elastic sealing cylindrical ring whose outer diameter abuts to body of sprayer. Other end and inner surface of dividing tube engage with threaded plug. Said plug is mounted telescopically by means of its cylindrical stem in dividing tube and it provides communication through duct and openings of duct of additional circuit of dividing tube with duct of fuel supply union of additional circuit. Between mounting flange and head body of sprayer is covered with heat insulation and with jacket.

EFFECT: enhanced operational reliability of fuel sprayer due to elimination of fuel carbonizing in ducts of sprayer and due to compensation of thermal deformation.

3 dwg

Description

The invention relates to fuel nozzles for injecting liquid fuel into a combustion chamber of a gas turbine engine.

Known fuel nozzle of the combustion chamber of a gas turbine engine with air spray, in which a thin continuous sheet of fuel is sprayed with a high-speed stream of air [RF Patent No. 2107177, F 02 C 7/22, 1998].

The disadvantages of this design are the increased dimensions, as well as increased emissions of harmful substances at the outlet of the combustion chamber due to unsatisfactory fuel atomization at reduced operating modes of the gas turbine engine due to low air flow rates.

Closest to the proposed invention is a fuel centrifugal dual-channel dual-circuit nozzle containing a housing with a nozzle mounting flange, as well as two fuel inlets located on the outside of the flange. At lower operating modes of the gas turbine engine, fuel is sprayed through the nozzle of the additional circuit, and at the main operating modes, the nozzle of the main circuit is turned on [D-30 aircraft dual-circuit turbojet engine. Technical description, M., Mechanical Engineering, 1971, p. 94, Fig. 94].

A disadvantage of the known design adopted for the prototype is the low reliability due to coking of the fuel in the low consumption auxiliary circuit channel made in the nozzle body from the side of the incoming air flow with high temperature and thermal deformation.

The technical problem that the invention solves is to increase the reliability of a fuel centrifugal double-circuit nozzle by eliminating coking of the fuel in the nozzle channels and compensating for its thermal deformation.

The essence of the invention lies in the fact that the fuel nozzle of the combustion chamber of a gas turbine engine, comprising a housing with channels and with fittings of the primary and secondary fuel supply circuits to the primary and secondary nozzles located in the nozzle head, as well as a mounting flange for attaching the nozzle to the outer housing of the combustion chamber, according to the invention additionally includes a dividing tube located inside the channel of the main circuit, inside which a channel of the additional circuit, a separator The end tube is fixed at one end in the nozzle head relative to the housing by a one-piece connection, and inside the body, from the outside of the mounting flange, between the fittings of the main and secondary circuits, a separation tube is mounted telescopically relative to the channel walls of the main circuit with a cylindrical protrusion and contacts one end with an elastic a sealing cylindrical ring in contact with the outer diameter with the nozzle body, and with the other end face and inner surface from the threads minutes plug telescopically mounted in a cylindrical shaft and a tube connecting the separation channel and the additional openings of the separation channel tube circuit with an additional circuit channel fuel feed nozzle, with a nozzle body between the mounting flange and the head is covered with thermal insulation and the casing.

In modern gas turbine engines, to increase efficiency, the compressor is executed with a high degree of compression, which leads to a significant increase in the air temperature at its outlet. For example, in a modern PS-90A engine, the air temperature at the compressor outlet in some modes reaches more than 600 ° C, which can cause overheating and coking of the fuel in the channels of the additional circuit with low fuel consumption.

Since fuel is supplied through the secondary channel in start-up modes, and in the main modes, starting with small gas, fuel is switched on through the main channel, the placement of the secondary circuit inside the main circuit channel eliminates coking of the fuel inside the secondary circuit channel and the coking of the fuel inside the main circuit the circuit does not occur due to increased fuel consumption through it, as a result of which the fuel flowing through it does not have time to overheat, which also contributes to the thermal insulation externally th surface of the nozzle body between the mounting flange and the head.

In the process of increasing the operating mode, the nozzle body, heating up from the compressor air, experiences thermal deformation, which, if it is rigidly fixed in the body, can lead to breakage of the separation tube. However, this can be avoided due to the fact that inside the case on the outside from the mounting flange between the fittings of the main and additional circuits from the other end, the separation tube is mounted telescopically relative to the walls of the main circuit with a cylindrical protrusion.

Contacting the dividing tube with one end face with an elastic sealing cylindrical ring in contact with the outer diameter with the nozzle body, and with the other end face and inner surface with a threaded plug, allows the cylindrical ring to elastically deform during assembly using a threaded plug, sealing the dividing tube along the end with increasing axial clearance δ between the cylindrical shank of the threaded sleeve and the tube, which increases the reliability of the fuel nozzle.

Due to the heat flows passing through the nozzle body, the heating of the ring can be significant, therefore, the placement of the sealing ring on the outside from the nozzle installation flange, i.e. outside the zone of exposure to compressor air allows you to reduce the temperature of this ring.

Figure 1 shows a longitudinal section of a fuel centrifugal dual-circuit dual-channel nozzle. Figure 2 shows the element I in figure 1 in an enlarged view, and in figure 3 - element II in figure 2 in an enlarged view.

The fuel nozzle 1 of the combustion chamber consists of a housing 2 with a mounting flange 3, designed to mount the nozzle on the outer housing (not shown) of the combustion chamber. On the outside of the flange 3 on the body 2, fittings 4 and 5 for supplying fuel to the main and additional circuits are installed, respectively, and on the inside of the flange 3 of the side of the outer surface 6 of the housing 2, thermal insulation 7 is installed, closed from the outside from air erosion by the casing 8.

In the housing 2, a channel for supplying fuel to the main circuit 9 is made, at the inlet connected to the internal channel 10 of the nozzle 4 for supplying fuel to the main circuit, and at the outlet through an inclined channel 11, cavity 12, openings 13, 14 and 15, a sprayer 16 in the nozzle head 17 1 - with the nozzle of the main circuit 18.

In the housing 2 of the nozzle 1 inside the channel 9 of the main circuit, a separation tube 19 is mounted, fixed with its inner end 20 in the head 17 of the nozzle 1 by means of a one-piece connection (soldering) 21, and its external end 22, located on the outside from the mounting flange 3, between with fittings 4 and 5 for supplying fuel to the primary and secondary circuits, using a cylindrical protrusion 23 is telescopically mounted in the channel 9 and is in contact with the end face 24 with an elastic sealing cylindrical ring 25 made of non-metallic material rial, for example, thermally expanded graphite, which maintains its working capacity without oxygen access up to 900 ° С. A cylindrical elastic ring 25 with its outer surface 26 is in contact with the outer surface 27 of the channel 9, and the inner 28 and side 29 surfaces with a threaded plug 30, mounted in the housing 2 with a thread 31 and telescopically mounted using a cylindrical shank 32 in the separation tube 19, connecting at the input channel 33 and holes 34 and 35 the internal cavity 36 of the fitting 5 for supplying fuel to an additional circuit with an axial internal channel 37 of the separation tube 19, at the output connected through a sleeve 38, an adapter 39 and a sprayer 40 with a nozzle 41 of an additional circuit.

This device works as follows.

When starting the combustion chamber of a gas turbine engine in a centrifugal nozzle 1, fuel is supplied to the fuel supply fitting 5 to an additional circuit.

Fuel flowing through the channel 37 of the separation tube 19, is sprayed using the atomizer 40 and the nozzle 41 of the additional circuit.

With an increase in the operating mode, fuel begins to flow into the nozzle 4 for supplying fuel to the main circuit, from where it passes through the annular channel 9 around the tube 19, through the inclined channel 11, cavity 22, openings 13, 14 and 15 to the main circuit atomizer 16 and nozzle 18.

With a further increase in the operating mode when heated from compressed air, the housing 2 of the nozzle 1 experiences a temperature deformation, which is compensated by the telescopic installation of the separation tube 19 relative to the channel walls of the main circuit with a cylindrical protrusion 23.

A sealing cylindrical ring 25, elastically deformed during assembly using a threaded plug 30, seals the tube 19 along the end face 24 with an increase in the axial clearance δ between the cylindrical shank 32 and the tube 19.

Claims (1)

A fuel nozzle of a combustion chamber of a gas turbine engine, comprising a housing with channels and with fittings of a primary and secondary fuel supply circuit to a primary and secondary nozzle located in the nozzle head, as well as a mounting flange for attaching the nozzle to the outer housing of the combustion chamber, characterized in that it further includes a separation tube located inside the channel of the main circuit, inside which a channel of the additional circuit is located, a separation tube at one end in the force head the unit is fixed relative to the housing by a one-piece connection, and inside the housing on the outside from the mounting flange, between the fittings of the main and additional circuits, a separation tube is mounted telescopically relative to the channel walls of the main circuit with a cylindrical protrusion and contacts one end with an elastic sealing cylindrical ring in contact with the outer diameter with nozzle body, and with other end and inner surface - with screw plug, telescopically mounted a second cylindrical shank tube and connects the separation channel and the additional openings of the separation channel tube circuit with an additional circuit for supplying fuel nozzle channel, wherein the sealing ring is made of a non-metallic material, and the nozzle body between the mounting flange and the head is covered with thermal insulation and the casing.

Images