The front unit of the combustion chamber for high temperature gte

 

(57) Abstract:

The front unit of the combustion chamber for high temperature gas turbine engine with a supply of fuel in the fuel reservoir through a fixed delimiters flow contains the front device made in the form of a series of corrugated plates. Profiled plate is installed at the entrance to the primary channels can move relative to each other in the circumferential direction when the change in the extent of flow sections of the primary channels. Each of the profiled plates consists of the fixed and movable parts are telescopically interconnected. The fixed portion of the telescopic plates rigidly fixed delimited stream. Return the moving parts of the plates mounted on the movable dividers flow. The fuel reservoir at one end with the inner ball joints fixed dividers flow, and the other end hinged to swing tagum, the second ends of which are pivotally attached to the movable dividers flow. This embodiment of the front of the device extends the range of stable combustion. 1 C.p. f-crystals, 6 ill.

The invention relates to a number of local front-line devices of the heating pipe of the combustion chambers of gas turbine engines, forming in front of the flame tube to the desired gas-dynamic flow structure in the form of a Central recirculation zone return currents (CRSMT). A. Lefebvre. The processes in the combustion chambers of the CCD. Moscow, Mir, 1986, S. 224.

The disadvantage of these front-line devices is the inability to control the flow of primary air due to their fixed geometry.

Closest to the proposed invention is a frontline unit of the combustion chamber for high temperature gas turbine engine with a supply of fuel in the fuel reservoir through a fixed flow dividers (Snee J. I. , Chinowsky J. C. Gas turbines, part two, Kiev. Head publishing Association "high school", 1977, S. 118-119, Fig. 88a).

The disadvantage of the front of the device of this combustion chamber is a low limit of combustion of the poor disruption of the flame in view of the fact that the intensity of the recirculation zones for collectors-stabilizers flame is low, and the dimensions of the generated Central recirculation zone return currents will be insufficient to provide a reliable stabilization of the flame. In addition, it is obvious that the method of supplying fuel through the collector-stabilisatoren combustion by poor breakdown of flame.

The present invention is to expand the range of stable combustion for controlled combustion temperature of the CCD.

This problem is solved due to the fact that the front unit of the combustion chamber for high temperature gas turbine engine with a supply of fuel in the fuel reservoir through a fixed flow dividers made in the form of a number of corrugated plates that are installed at the entrance to the primary channels can move relative to each other in the circumferential direction when the change in the extent of flow sections of the primary channels, each of the plates consists of a fixed and movable parts, telescopically interconnected, and the fixed portion of the telescopic plates rigidly fixed dividers thread, and return the moving parts of the plates on the movable dividers flow. The fuel reservoir at one end with the inner ball joints are fixed to a stationary flow dividers and the other swivel fixed swivel rods, the second ends of which are pivotally attached to the movable dividers stream.

In Fig. 1 shows the combustion chamber is high the location of the primary, secondary channels and nozzles corresponding to the maximum mode, and Fig. 4 - the same, but corresponding to the minimum mode, and Fig. 5 - telescopic connection plates; Fig. 6 is a top view of the fuel manifold.

The front of the device 1 of the combustion chamber high temperature of the CCD 2 contains a number of profiled plates 3, each of which consists of a fixed 4 5 and the movable parts are telescopically interconnected. The fixed part 4 of the telescopic plates rigidly fixed 6 dividers flow reactor high-temperature zone of the combustion chamber 2, and the return of the movable part 5 plates on moving 7 the delimited stream. Supply of fuel to the nozzles 8 through collectors 9 at one end with the inner ball joints 10, fixed to a stationary 6 dividers threads, and the other with swivel fixed swivel rods 11, the second ends of which are pivotally attached to the movable 7 separators flows. The fuel supply to the reservoir 9 through a fixed 6 separators flows, which are provided with a fuel channel 12.

When working a high-temperature combustion chamber 2 at the maximum power mode under primary air. Front of unit 1 primary channels in this case also have a maximum size, and the nozzles 8 are located in the Central part of the primary channels (Fig. 3).

At the transition of the combustion chamber on the lower modes (Fig. 4) the bandwidth of the primary channel, and hence the area of the front of the device 1 gradually decreases, and accordingly increases the throughput of the secondary channels. However, given the increased intensity ZRZUT due to the increase of the intensity of the jets of secondary air and reduce the transverse dimensions of the primary channels, nozzles 8 are located at some distance from the Central part of the primary channels, providing a more complete their "cover".

This embodiment of the front of the device allows you to extend the range of stable operation of high-temperature combustions chambers GTD poor disruption of the flame by creating a large Central recirculation zone return currents in each of the primary channel and the ability to control where a supply of fuel.

1. The front unit of the combustion chamber for high temperature gas turbine engine with a supply of fuel in the fuel reservoir through NENO plates, installed at the entrance to the primary channels can move relative to each other in the circumferential direction when the change in the extent of flow sections of the primary channels, each of the plates consists of a fixed and movable parts, telescopically interconnected, and the fixed portion of the telescopic plates rigidly fixed dividers thread, and return the moving parts of the plates on the movable dividers stream.

2. The front of the device under item 1, characterized in that the fuel reservoir at one end with the inner ball joints are fixed to a stationary flow dividers, and the other swivel fixed swivel rods, the second ends of which are pivotally attached to the movable dividers flow.

 

Same patents:

The invention relates to the field of engine construction and can be used in combustion chambers of gas turbine engines

The invention relates to energy, transport and chemical engineering and can be used in gas turbines

The invention relates to aircraft engine industry, in particular to devices for regulating the swirl of the front unit of the combustion chamber

The invention relates to the turbines, in particular to the combustion chambers of gas-turbine units (GTU)

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

FIELD: gas turbine engine engineering.

SUBSTANCE: combustion chamber comprises housing provided with inner and outer ring shells, device for graduate change of the ratio of areas of the cross-sections of primary and secondary passages, and collector stabilizer. The reaction zone has shutters and inserts that define inner and outer rings. The shutters and inserts are pivotally interconnected for permitting change of the area of the cross-section in radial direction. The collector stabilizer is unmovable.

EFFECT: enhanced reliability.

4 dwg

FIELD: engines and pumps.

SUBSTANCE: device to control a low emission combustion chamber of a gas turbine, specifically of gas turbine assemblies, comprises case with channels supplying primary and secondary air into a flame tube of the combustion chamber and with a channel for mixing basic fuel with primary air, wherein this channel an axial swirler and synchronous adjustment devices to control consumption of primary and secondary air are installed. The devices of synchronous adjustment of consumption of primary and secondary air are installed in corresponding channels of the case and interconnected with each other so that at an increase or decrease of primary air consumption correspondently causes an increase or decrease of secondary air consumption. An initial portion of the flame tube is made as an intake diffuser. A device to control consumption of primary air is made as a flame stabilizer and installed with a possibility to axial displacement in intake diffuser of the flame tube; at that it is connected to the regulator of basic fuel to maintain ratio of surplus air in the primary air supply channel and in the mixing channel constant or close to constant within ranges from 1.7 to 2.5. The blades of the axial swirler are arranged concentric at an angle to its axis bigger or equal to 30°. A nozzle with a critical section is installed at the outlet from the combustion chamber.

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).

EFFECT: invention allows to regulate primary air supply to the combustion chamber section during equipment operation, burning device design simplification, it operation safety stays constant, possibility of device change on the running gas turbine equipment.

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 0.80.4, and flow velocity coefficient in flame tube holes is 0.220.1.

EFFECT: invention provides maximum economy, reliability and service life of engine.

5 dwg

FIELD: engines and pumps.

SUBSTANCE: diffusion chamber of gas turbine engine is arranged between external case and internal case of engine, supplied with air through inlet diffusion channel and includes combustion chamber of convergent type. Combustion chamber restricts external annular channel with external case and internal annular channel with internal case. Diffusion chamber includes the fairing partially covering external annular channel. Fairing includes the housing made in the form of round part formed with rotation about fairing axis. Housing is located between two planes which are essentially transverse to the above axis of fairing and has plane section. Also, the housing includes radial external end and radial internal end. Fairing includes external side starting from the above radial external end and radial internal side starting from radial internal end, as well as fasteners intended for its fixture on combustion chamber. The other objects of this invention is combustion chamber located in the above diffusion chamber, as well as gas turbine engine containing such diffusion chamber.

EFFECT: invention allows reducing pressure losses.

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.

EFFECT: ruled out carbon monoxide, almost completely, from engine exhaust gases, more complete fuel combustion.

10 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed combustion chamber comprises housing accommodating the perforated fire tube with combustion and dilution zones, fuel feed system, air primary and secondary flow feed system and fuel-air mix ignition system. Airflow feed system incorporates primary airflow controller in primary air channel and secondary airflow controller inside circular channel between combustion chamber walls and fire tube. Said controllers include laser radiation source, laser radiation splitter for primary and secondary airflows controllers. Every said controller incorporates optic fibres with inputs connected to laser radiation splitter. Output of primary airflow controller optic fibre is connected via through hole with primary airflow inlet channel equipped with at least two opposed mirrors. Secondary airflow controller comprises at least two opposed mirrors located inside circular channel, one of the mirrors having a through hole at mirror axis in focal plane. Output of secondary airflow controller optic fibre is connected via mirror through hole with circular channel. Laser source can excite oxygen molecules to metastable singlet states.

EFFECT: higher completeness of combustion and chamber efficiency.

16 cl, 3 dwg

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.

3 dwg

Up!