Device for fuel combustion in gas-turbine engine

FIELD: fuel combustion device for gas-turbine engines.

SUBSTANCE: proposed device has case, as well as fixed and movable flow separators wherein fuel is supplied to flame-stabilizing fuel manifolds built of fixed and movable parts and provided with coaxial holes. Movable sleeve is inserted in movable part of stabilizing manifold. Holes are disposed in movable part of stabilizing manifold and in sleeve at right angle to stabilizing manifold axis, and in fixed part holes have their sectional area contracting toward outlet. Springs are installed between movable part of stabilizing manifold and sleeve.

EFFECT: enhanced operating efficiency of combustion chamber throughout entire operating range of engine.

1 cl, 5 dwg

 

The invention relates to combustion chambers of continuous action, use liquid fuel, namely the means of stabilization of the flame.

A device for burning fuel in a gas turbine engine (GTE), which includes a housing with a circular shells, fixed and movable dividers threads forming the primary and secondary channels, and a stationary separator flows made channels for supplying a fuel to the fuel reservoir, stabilizers flame, which is installed at the entrance to the primary channels and consist of fixed and moving parts are telescopically interconnected and rigidly fixed respectively on the fixed and movable dividers flows. In the stationary and moving parts of the collectors stabilizers flame holes of the burner. [1]

The disadvantage of this device, taken as a prototype, is the impossibility of efficient organization of the processes of mixing the fuel-air mixture (FA) in a wide range of combustion chamber (CC).

An object of the invention is to expand the range of effective work of the COP due to improvements in apparatus for burning fuel in the CCD by creating collector-stabilizer that allows you to control the spray angle.

The invention consists in that the device for burning fuel, comprising a housing, stationary and movable separators flows, where the fuel is supplied to the fuel reservoir, stabilizers flame, consisting of fixed and moving parts with them in aligned holes in the movable portion of the collector-stabilizer inserted movable sleeve, and the movable part of the collector-stabilizer and the sleeve openings are at right angles to the axis of the collector-stabilizer, and a fixed part of the holes are tapered toward the exit section, in addition, between the movable part of the collector-stabilizer and sleeve springs installed.

The technical result of the invention is to expand the range of effective operation of the combustion chamber that is provided by a control spray angle of fuel in dependence on operating parameters of the engine. The influence of air velocity on the process of atomization in the combustion chambers of aircraft gas turbine engines significantly because this process is not completed on a section of the nozzle, it lasts in the environment as long as the size of the drops will not reach the minimum critical value, below which its decay becomes impossible. The critical droplet size depends not on the absolute and the relative magnitude of the fluid velocity in the environment. If the liquid and gas move in the same direction of the tion, the range of the jet is increased, and the atomization deteriorates, resulting in higher average diameter of the drops. On the contrary, when the movement of liquid and gas in opposite directions, the range of the jet is reduced, the cone of the flame is increased, and the quality of atomization is increased.

If the spray angle is oriented normal to the flow direction of air, then drops larger penetrate into the flow at a greater distance. With this distribution of aerosol ignition easier if it is done in the field of small drops.

Therefore, in the inventive device at minimum power to ensure stable combustion, the fuel injection is carried out at a right angle to the axis of the collector-stabilizer that allows you to create local zones of enriched fuel. This promotes efficient combustion process and stabilize the flame at low pressure at the entrance to the COP. When switching to the maximum angle modes of fuel injection is changed in the direction opposite to the direction of air flow. This improves the dispersion of the fuel Assembly due to collision and crushing drops of fuel with incoming air; to prevent the demolition drops down to the stream for the collector-stabilizer at high speed stream.

To determine the effect of all dimensional parameters defining the process the atomization of the fuel, we will use the empirical equation volumetric spectrum atomization:

where Vs- total relative volume, i.e. the sum of the relative volume of all droplets with diameter less than or equal to the drops andi;

, n are constants and size distribution, respectively.

Equation 1 expresses the curve of probability density of the distribution of volumes of liquid for different droplet sizes in the spectra of atomization. Taking into account the impact of changes in the angle of the spray of fuel and flow spectra atomization will take the following form (1, 2).

Based on the ratio of the flow velocity and the velocity of the fluid that can be injected into this flow, optimal spray angle, which ensures the efficient atomization, will be determined according to the schedule according to the change in the angle of spray of fuel from the flow velocity (figure 3). [2, 3]

The achievement of the technical result of the invention is provided by the presence of distinctive features, namely the following structural elements in the device:

- movable sleeve mounted in the movable part of the collector-stabilizer;

- springs are installed between the movable part of the collector-stabilizer and the movable sleeve;

- holes located in under IGNOU and stationary parts of the collector-stabilizer and the sleeve at right angles to the axis; in the fixed portion of the cross section of the holes is tapered towards the outlet,

that allows to make a conclusion about the presence of patentability criterion of "novelty".

In the known technical solutions these distinctive characteristics have been identified that meet the criteria of the invention "significant differences".

Figure 1 - range of atomization when changing the spray angle α; figure 2 - range of atomization when changing the spray angle α and the flow velocity ω; figure 3 - dependence of the change of the angle of spray of fuel from the flow velocity; figure 4 presents a device for burning fuel in the CCD cross section; figure 5 - collector-stabilizer cross section.

The device (figure 4) consists of a casing 1, 2 fixed and 3 mobile separators flow, collector-stabilizer 4.

Collector-stabilizer 4 (figure 5) is a body consisting of a fixed 5 and mobile 6 piece collector-stabilizer 4 with the movable sleeve 7, forming a cavity Between A. movable part collector-stabilizer 4 and the sleeve 7 the springs 8. In the movable sleeve 7 and the casing is made of coaxial holes 9 and the fixed part 5 of the housing holes are narrowed toward the exit.

Description of the device

The air supplied into the combustion chamber, is arranged in the reactor zone on the primary and secondary rela is Oseni, defined bandwidth of the primary and secondary channels. The combustion process is carried out by supply and stabilize the flame by collectors stabilizers 4.

When the working temperature of the CCD at low power mobile sleeve 7 collector-stabilizer 4 is retained by the spring 8 in the position in which the fuel injection is made at a right angle to the incident flow.

When switching to modes of higher power increases the fuel pressure in the cavity And collector-stabilizer 4, thus moving the movable sleeve 7, thereby changing the relative position of the holes 9, which allows for changing the spray angle of fuel.

The proposed solution improves the efficiency of fuel combustion in a wide range of gas turbine engines work.

Sources of information

1. RF patent №2124676, CL F 23 R 3/26, publ. 10.01.1999,, bull. No. 1 (prototype).

2. Lefebvre A. Processes in combustion chambers of the CCD. - M.: Mir, 1986, s...473.

3. Rauschenbach BV and other Physical basis of the working process in the combustion chambers of jet-propulsion engines. - M.: Mashinostroenie, 1964, p.53...173.

Device for burning fuel in a gas turbine engine, comprising a housing, stationary and movable separators flows, where the fuel is supplied to the fuel Kollek, the ora-stabilizers, flame, consisting of fixed and moving parts, made them aligned holes, characterized in that the movable part of the collector-stabilizer inserted movable sleeve, and the movable part of the collector-stabilizer and the sleeve openings are at right angles to the axis of the collector - stabilizer, and a fixed part of the holes are tapered toward the exit section, in addition, between the movable part of the collector-stabilizer and sleeve springs installed.



 

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FIELD: fuel combustion device for gas-turbine engines.

SUBSTANCE: proposed device has case, as well as fixed and movable flow separators wherein fuel is supplied to flame-stabilizing fuel manifolds built of fixed and movable parts and provided with coaxial holes. Movable sleeve is inserted in movable part of stabilizing manifold. Holes are disposed in movable part of stabilizing manifold and in sleeve at right angle to stabilizing manifold axis, and in fixed part holes have their sectional area contracting toward outlet. Springs are installed between movable part of stabilizing manifold and sleeve.

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FIELD: gas turbine engine engineering.

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4 dwg

FIELD: engines and pumps.

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EFFECT: device allows to extend the range of stable operation and adjustment of a combustion chamber, to reduce a possibility of self excited oscillation of pressure in a combustion chamber and to reduce harmful exhaust.

4 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine combustion chamber contains a casing with an annular flame tube incorporating two spaced apart annular shells jointed together by the front wall streamwise first part, the said wall being furnished with heat-insulating screens arranged on the combustion space side. The said heat-insulating screens contain flanges and ribs on the side facing the front wall provided with the holes for the burner modules to be installed therein and for cooling air to pass through. The rib and flange, on every heat-insulating screen, are enclosed along the outline. The heat-insulating screen surface with the rib and the front wall form a space communicating, via the burner module holes, with the flame tube space. The flanges of adjacent heat-insulating screens together with the front walls form flowing channels. The front wall cooling air passage holes are arranged along the outline of every heat-insulating screen on both sides of a rub. The flange side facing the combustion space continues the screen surface.

EFFECT: low power engine, complete fuel combustion and reliable combustion chamber.

3 cl, 3 dwg

FIELD: heating.

SUBSTANCE: invention related to energy, particularly to burner devices and can be used in gas turbine equipment. Burner device consists of a case (1), a fuel nozzle (2), a front device (3), a fire tube (4). The burner device belongs to gas-turbine engine combustion chamber. The front device executed with holes for fuel nozzles installation (2). The fire tube (4) with the front device (3) located inside of the combustion chamber cage (5). Fuel nozzles (2) connected to a gas ring collector (6). In combustion chamber fire tube and cage (5) between wall area air nozzles (7) located radically. Air nozzles (7) connected to the common ring air collector (9). The air collector (9) located in the case (1).

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1 dwg

FIELD: power industry.

SUBSTANCE: combustion chamber includes housing, flame tube with air supply holes to combustion and mixing zones, and front device with air swirlers and fuel feed atomisers. Flame tube of combustion chamber has geometrical and gas-dynamic criteria providing its optimum operating mode. Ratio of cross midlength section area to total effective surface area of all holes is 7.0 ±1.5. Relative carrying capacity of swirlers is 0.17 ±0.1. Air flow swirling intensity with swirlers of front device is 0.8±0.4, and flow velocity coefficient in flame tube holes is 0.22±0.1.

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5 dwg

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14 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed combustion chamber comprises housing, fire pipe with combustion and dilution zones, fuel feed system, primary and secondary air flows feed system. The latter comprises the device to act on secondary air flow inside circular channel between combustion chamber and fire pipe walls. Besides, it includes fuel-air mix ignition device. Said device to act on secondary air flow inside circular channel comprises laser radiation source, optical fibre and at least two opposed mirrors arranged inside said channel. One of said mirrors has through bore at focal line. Laser radiation source can excite molecular oxygen to singlet state and is connected via optical fibre with through bore of the mirror.

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FIELD: engines and pumps.

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FIELD: engines and pumps.

SUBSTANCE: device to burn fuel in a gas turbine engine comprises outer and inner bodies forming a circular cavity, where fixed and mobile flow separators are installed, forming alternating primary and secondary channels. On the outer body of the circular cavity in each primary channel there are symmetrical rectangular cuts corresponding to its size, with fixed flow separators passing through them. In the end part of the circular cavity there are two rings installed as capable of rotation around the longitudinal axis, the diameter of one of which corresponds to the diameter of the outer body, of the second one - the diameter of the inner body. On the outer ring there are 2N slots, where N - natural even number corresponding to the number of primary channels. In each primary channel there are two plates installed, being made according to the profile of the wing and hingedly fixed on the inner ring, with the possibility of displacement along the longitudinal axis of the engine along the slots on the outer ring and around their central axis. The slot length corresponds to plate travel from minimum to maximum size of the primary channel. In each primary channel there are angular flame stabilisers installed with an opening angle of 55-65 degrees in direction of the flow, which are rigidly fixed on the outer and inner rings as equidistant along the circumference. The point of fixation on the outer ring is between the slots of the appropriate channel.

EFFECT: invention is aimed at expansion of the range of combustion chamber stable operation.

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