The diffuser main combustion chamber of aircraft gas turbine engine
(57) Abstract:The diffuser main combustion chamber of an aviation gas turbine engine includes a housing with spaced therein telescopic rings and diffuser channel. Diffuser channel formed near telescopic rings connected by clamps. The clamps are installed with the possibility of changing the shape of the diffuser channel depending on the operation mode, taking the form either sugraduotoje or channel with a sudden expansion. This embodiment of the diffuser increases its efficiency at various operating modes of the gas turbine engine. 3 Il. The invention relates to the field of turbine construction, in particular to the diffusers main combustion chambers (ACS) aviation gas-turbine engines (GTE).To reduce the speed of the air entering the flame tube OAKS and converting part of the kinetic energy in the increase of static pressure diffuser is used .Known steady airflow diffuser aerodynamic type with shaped channel that provides the lowest loss of total pressure and the greatest uniformity of the velocity field .Moreover, the increase in the area section consists of outer and inner housings, forming the channel of the diffuser. The opening angle of the cone from 7 to 12 degrees .The main disadvantages of this cone are: a large length, which undoubtedly affects the mass characteristics of the engine, and sensitivity to change of the velocity profile at the entrance.The analysis of the literature [1, 2, 3] shows that the most effective is the cone with the regulatory elements of the flow regime. The most widely diffusers with boundary layer suction to reduce its thickness as a means to prevent separation of the flow in diffusers with large angles. The main difference from the aerodynamic diffuser - increased angle that puts the problem of boundary layer suction, generated by the increase of the opening angle is above 12 degrees, to prevent separation of the flow and the occurrence of stagnant areas.The primary and main shortcomings of the existing diffusers is the inability to control their modes of operation of the CCD in order to achieve maximum efficiency. Slits for air suction it would be best to place directly prior to the expected point of flow separation. However, since the position of the point from The closest to the proposed invention is a diffuser main combustion chamber of an aviation gas turbine engine, comprising a housing located therein telescopic rings, diffuser channel .The disadvantage of it is the inability of its regulation depending on the operation mode of the CCD.Task to be solved by the present invention is directed, is to increase the efficiency of the diffuser in a wide range of engine operating conditions. The real solution to this problem is the creation of the diffuser with adjustable angle and controlled by boundary layer suction.The problem is solved due to the fact that the diffuser main combustion chamber of an aviation gas turbine engine, comprising a housing located therein telescopic rings, diffuser channel formed near telescopic rings connected by clamps installed with the possibility of changing the shape of the diffuser channel depending on the operation mode, taking the form either sugraduotoje or channel with a sudden expansion.This embodiment of the cone leads to the possibility of regulation Cana is the main section for exhaust air from the diffuser.In maximum mode and when running it is necessary that the dimensions of the tear-off zones, loss of total pressure were minimal, and the pressure distribution was uniform. For this it is advisable to use a diffuser with a sudden expansion. This provides a lower sensitivity of the velocity profile at the exit of the diffuser to changes in the velocity profile of the input, which is an important advantage in cases where the velocity profile at the exit of the compressor depends on the mode of operation of the engine and operating conditions .On the lower modes, it is advisable to have togravity diffuser, which ensures minimum losses associated with flow separation, and less asymmetry and irregularity of the flow .In Fig. 1 shows a General view of the diffuser when it is working at full speed, longitudinal section; Fig. 2 - the same, when running on low power modes; Fig. 3 - section a-a in the rotated position.The proposed diffuser includes a housing 1 with telescopic rings 2, 3 tabs, the axial actuator 4, the cylinder rod 5, the profiled hole 6, which can move the tabs 3.When the engine is running and when his work on m is with sudden expansion. The gap formed between the telescopic rings are slots for exhaust air from the zone with high blood pressure. The total area of the formed slits is selected so that the exhaust air does not exceed 3-4% of the total air flow. According to  the air suction within the specified limits can significantly improve the efficiency of the diffuser with sudden expansion and bring him on such an important parameter as the ratio of total pressure recovery to sugradjanina the diffuser. When changing the mode of operation associated with a decrease in air flow by means of the axial actuator 4 is the extension of telescopic rings 2, while the axial actuator acts on the front ring, and through the latches 3 in axial movement involved the rest of the ring 2. Thus there is a gradual decrease in the area of flow sections of the slits and the desired reduction of the flow of the suction air. When the engine is at low modes form a cone - segregata, slits for air suction is missing.The use of the diffuser elements of the regulation allows you to:
first, to choose the optimal shape of the channel depending on the operation modes;
secondly, the maximum mode, by increasing the distance from the sudden expansion to the reaction zone, to reduce the flow velocity, which positively affects the combustion process in the combustion chamber.Sources of information
1. A. Lefebvre. The processes in the combustion chambers of the CCD. M.: Mir, 1986, S. 94, 115.2. Mayorov, A. I., Yagodkin C. I. Methodology and the results of calculations of flows in channels with sudden expansion. Proceedings of CIAM, N 883, 1980.3. M. E. Deitch, A. E. Zariankin. Fluid dynamics. M.: Energoatomizdat, 1984, S. 282, 283.4. EP 0100135 A1, IPC 6 F 23 R 3/26, 1984, Fig. 3,3 century The diffuser main combustion chamber of an aviation gas turbine engine, comprising a housing located therein telescopic rings, diffuser channel, characterized in that the diffuser channel formed near telescopic rings connected by clamps installed with the possibility of changing the shape of the diffuser channels depending on the operation mode, taking the form either sugraduotoje or channel with a sudden expansion.
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.