The combustion chamber of a gas turbine engine with adjustable airflow
(57) Abstract:The combustion chamber of a gas turbine engine with adjustable air distribution contains a heating pipe with Windows in the wall, overlapping placed at the location of the Windows of the movable element. The movable element is designed as a flexible tape covering the heating pipe and having at least one slit. With a system of levers with the drive connected sections of the tape, and it provides radial movement of the tape. This embodiment of the combustion chamber increases the reliability of its work and provide the desired air distribution over the length of the combustion chamber. 4 Il. The invention relates to combustion chambers (K. C.) gas turbine engines (GTE), in particular to K. C. with adjustable airflow.Due to stricter requirements for emissions of harmful substances GTE (carbon monoxide - CO, unburned hydrocarbons, CnHm, oxides of nitrogen (NOx) there is a need to develop K. S. low emissions of these substances. Among other solutions (steam or water in K. S.) apply the redistribution of air flow along the length of the K. C. for optimal combustion conditions over the entire operating range of modes Lenogo run K. S. reduce the air flow in the primary zone, and the high modes to prevent the formation of NOxincrease the air flow in the primary zone.The known device K. C., which distribute air along its length (for example, patent N 4534166 USA, which use adjustable swirl device in front of K. S.; patent N 4050240, USA, in which the flame tube placed swivel belt overlapping Windows; patent N 4594848 USA where to overlapping Windows in the flame tube applied rings, movable along the axis K. S.Closest to the camera is the combustion chamber of a gas turbine engine with adjustable airflow containing heating pipe with Windows in the wall, covered and placed in the location window movable element connected through a lever system with actuator (EP 0100135 A1, IPC 6 F 23 R 3/26, 1984).A disadvantage of the known devices is their low reliability, since the heating of the walls of the flame tube rotatable and movable along her rings, belts or ensure tightness (when closed) that does not regulate optimal air distribution along the length of the flame tube, or if duntov due to wrinkling of the flame tube, especially when its uneven heating and thermal expansion of the flame tube and the adjustable elements.The objective of the invention is to reduce emissions of harmful substances, improving the reliability of the device controlling the flow of air and simplifying the design.The problem is solved due to the fact that in the combustion chamber of a gas turbine engine with adjustable airflow containing heating pipe with Windows in the wall, overlapping placed in the location window movable element connected through a system of levers to drive the movable element is designed as a flexible tape covering the heating pipe and having at least one section, with a system of levers connected sections of the tape, and it provides radial movement of the tape.In Fig. 1 shows a longitudinal section of the combustion chamber;
in Fig. 2 shows a section of an adjustable device along a-a of Fig. 1;
in Fig. 3 shows a section of an adjustable device In Fig. 2;
in Fig. 4 shows the sealing of the controlled device, view C-C of Fig. 3.In case 1, the combustion chamber is placed the flame tube 2 having, in addition to other, at least od is a crowded place, the ends of which are movably (pivotally) connected via a rocker arm 5, earrings 6 and rod 7 with the actuator (e.g., pneumatic, electric, etc). On the flanging (thick edges) window 3 made of the grooves 8. Before the location of the tape 4 and posted by the guide ribs 9 with 10 Windows.The device operates as follows.In the run mode of the CCD and low operating modes, the tape 4 is translated draft 7 through the plug 6 and the yoke 5 in the upper position (shown in Fig. 2 is shown in dashed lines). The air through the window 10 and 3 passes (bypassed) inside the flame tube, on its output, the consumption of air in the primary zone of the flame tube 2 is reduced, which creates favorable conditions for the ignition (start) and sustained combustion of fuel-air mixture in the primary zone with high combustion completeness, i.e. with a small amount of unburned CnHmand low education CO. (These modes due to low temperatures and air pressure at the entrance to K. C. nitrogen oxides are not formed.) With the increase of engine operation mode and maximum mode, the tape 4 is translated into a lower position, i.e. in contact with the flared Windows 3, providing a guaranteed fit and tightness, blocking Dosi located in the primary zone, increases Zapadnaya mixture in it. In the closed position, the tape is regulated flow of air enters the flame tube through the slots 8 for cooling the ribbon 4 and the walls of the flame tube 2 around holes 3. Given the fact that NOxformed at temperatures in excess of 1650oC, the composition of the mixture in the primary zone to provide in such a way that the temperature in the combustion zone does not exceed the above, which is achieved by selection of the areas of openings in the wall of the flame tube of the primary zone and the 3 Windows.Thus, the use of the device with the movement of the tape 4 in the radial direction will simplify design, increase reliability and provide the desired air distribution along the length of the combustion chamber, and hence the small emissions of harmful substances in the entire range of the CCD. The combustion chamber of a gas turbine engine with adjustable airflow containing heating pipe with Windows in the wall, overlapping placed in the location window movable element connected through a system of levers with the actuator, wherein the movable element is designed as a flexible tape covering the heating pipe and having at least one incision with systems
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.
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
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.
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.
EFFECT: invention provides maximum economy, reliability and service life of engine.
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.