Oil system of power gas turbine unit |
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IPC classes for russian patent Oil system of power gas turbine unit (RU 2535518):
 Elastic-damper support of turbojet engine / 2534686
Elastic-damper support of a turbojet engine includes an inner bushing connected with a C-shaped elastic element, a support ring and a rear flange of the labyrinth. The support ring is made as a whole with the rear flange of the labyrinth. Between the support ring and the inner bushing there is a perforated intermediate bushing. And between the perforated intermediate bushing and the inner bushing there is a damper cavity. Holes of the intermediate bushing are made as capable of communicating circular channels of oil supply in the support ring with a slot damper cavity. Radial ledges on the rear tail of the intermediate bushing are engaged with axial ledges of the rear tail of the inner bushing. On the radial rib of the perforated intermediate bushing there is an oil supply jet, which is L-shaped in the cross section. The radial tail of the jet is arranged between composite parts of the C-shaped elastic element.
 Turbine of double-rotor gas turbine engine / 2534339
Turbine of a double-rotor gas turbine engine comprises an external body, an air header, a pre-oil and an oil cavities, rotors of high and low pressures, channels of oil supply into roller bearings, oil seals, a wheelspace labyrinth seal, feed nozzles. In accordance with the stated proposal the turbine is equipped with a support circular shell with a radial collar, a circular nut with a radial collar on its side surface, a support bushing and a radial-end oil seal. The support bushing is installed on the shaft of the high pressure rotor and is fixed by a circular nut. The support circular shell is made as a whole with the shaft of the low pressure rotor and is installed to form an upper oil bath. The radial-end oil seal is made in the form of two step-bearings with graphite sealing rings and a spacer bushing with a fixing spring arranged between them. Oil seals between the pre-oil and oil cavities are made in the form of bracelet graphite seals. In the support circular shell and in the step-bearing adjacent to the end of the shaft of the low pressure rotor there are holes communicated with each other. The circular nut is installed to form a middle oil bath. Feed nozzles are placed opposite to the middle oil bath.
 Breathing system of turbojet engine / 2532393
Invention relates to turbojet double-circuit engines used in the field of aviation. A breathing system of a turbojet engine includes a breathing pipeline connected with a breathing pipe installed onto a nozzle. The outlet end of the breathing pipe is made as bent to form a reservoir for oil condensate. The outlet section of the nozzle is made as perpendicular to the axis of the pipe.
 Oil system of aviation gas turbine engine / 2530968
Invention relates to the field of aviation propulsion engineering, namely, to devices of oil systems of aviation gas turbine engines. The oil system of the aviation gas turbine engine comprises driving centrifugal air separator and a breather installed in pumping and breathing manifolds. The centrifugal air separator and breather are arranged coaxially on one driving shaft and are made in a single body. The manifold of air exhaust from the centrifugal air separator is arranged inside the driving shaft and is connected to the input of the centrifugal breather.
 Oil system of aircraft gas turbine engine with afterburner / 2529280
For the purpose of improving the efficiency of oil cooling in an oil system, cooling capacity of fuel delivered to the afterburner in the course of engine operation in reheat power mode, is used in a fuel-oil heat exchanger. For the above the fuel-oil heat exchanger is made in the form of two sections in which fuel cavities in heat exchanging matrices are made as separate ones and are connected to different fuel supply main lines (to the main chamber or afterburner), and the oil cavities are communicated with each other via a controlled two-position distribution valve.
 Assembly of gas turbine engine rotor / 2528789
In assembly of proposed rotor it is fitted in rolling bearing assemblies. One of said assemblies is composed by roller bearing with oval racer engaged by power elements with engine stator. Bearing is fitted at the support so that larger axis of racer is aligned with rotor gravity force direction. Note here that support stiffness and racer oval parameters are selected proceeding from relationships protected by this invention.
 Turbine support / 2525383
Support for a turbine of a gas turbine engine comprises a bearing (4), a shaft (6) and a labyrinth (11) with a flange (10) between the bearing (4) and the turbine disk (8). An additional flange (12) is set on the outer side of the labyrinth (11) flange (10) forming a blowdown cavity (13). The cavity (13) at its inlet is connected to the air cavity (14) of the housing of the shaft (15) and at its outlet - to the inner cavity (20) of the shaft (6) through the grooves (17) and channels (18) in the labyrinth (11) and (19) in the shaft (6) which are inclined in respect to the support (1) axis (16). The grooves (17) from the inlet (21) to the outlet (22) are oriented in the direction (23) of the shaft (6) rotation. A baffle plate (25) with bayonet-type mount (26) of the inner tail (27) on the additional flange (12) forming a slot air cavity (28) is installed on the external side of the additional flange (12). The support labyrinth (31) which is the closest to the turbine disk (8) is made with sealing microridges (34) on the working surface (35) of the rim (33) with increased thickness. The relation of the microridge (34) height h to the value of the radial clearance δ in the labyrinth (31) being the closest to the disk (8) falls within the range 1.5-2.5. The relation of the maximal diameter D of the labyrinth (31) being the closest to the disk to the minimal thickness H of the labyrinth (31) rim (33) falls within the range 20-40.
 Starting gas turbine engine by contactless salient-pole sync generator with rotating rectifier / 2524776
At initial period of gas turbine engine starting, primary generator armature winding and exciter excitation winding are connected via control unit to power supply. Note here that said control unit allows primary generator magnetic flux vector advance relative to rotor pole axis while gas turbine engine is accelerated by reactive moment. As rpm increases, induced e.m.f. in exciter armature winding rectified by rotating rectifier feeds the primary generator excitation winding to generated active torque. At reached preset rpm control unit is disconnected from primary generator winding while contactless salient-pole sync generator changes over to generator mode.
 Device to lubricate journal bearing of turbomachine rotor / 2522748
Feature of the proposed design is the usage of a hydraulic motor to drive an extraction pump set inside an oil sump of a rotor journal bearing, the said motor is operated by the energy of oil supplied for the lubrication of the rotor journal bearing. For this purpose the extraction pump in the oil sump of the rotor journal is designed as a two-section one. The sections are connected kinematically and isolated hydraulically from each other. One of the pump sections serves as a hydraulic drive for the other one, for this purpose its oil sump is sequentially included in the oil supply mains to the discharge manifold of oil supply. As a rule, the oil supply pressure exceeds the oil pressure in the extraction mains by several times, thus it is possible to convert a part of potential energy of the oil supply pressure into kinematic energy of the rotation of the extraction pump gear wheels.
 Aircraft gas turbine / 2522713
Oil-air emulsion with high content of air is formed at discharge pump inlet at extreme engine operating conditions (for example, at aircraft acrobatic flights) due to increase in hydraulic resistance in discharge lines, increased mixing of oil with fuel and intensified dissolution of air in oil. This can result in decrease in lift and discharge pump efficiency, discharge pump being a reliable component of oil system. Problem pump oil chamber feed and discharge balance is disturbed to overfill said chamber and to overheat the oil. Both indications are accompanied with oil leaks from oil tank that brings about the engine "oil hunger" conditions.
 Gas-turbine engine oil system with continuous redundancy device / 2244141
Invention is aimed at creating recirculation oil systems in which reservoir oil is repeatedly used for lubrication and cooling of supports, and overfilling of supports in case of failure of main oil system is prevented. According to invention, oil system of gas-turbine engine with continuous redundancy device contains space of at least one support rotor accommodating main and additional nozzles, main and additional oil tanks breathers, shutoff valve with control and operating spaces and delivery and pump-out main lines. Main oil tank communicates with delivery main line with main nozzles, control space of shutoff valve and additional oil tank with bottom part and communicating with additional nozzles. Oil system includes reducer space. Space of one support is combined with space of reducer to form common space having bottom and central parts. Additional nozzles and additional oil tank are located in central part of common space. Additional oil tank communicates with main oil tank through jet. Shutoff valve is located in bottom part of additional oil tank and its operating space can communicate with additional oil tank and with central part of common space. System has second similar shutoff valve installed in common space under additional oil tank. Valve control space is connected with main oil tank delivery main line, and operating space is connected with bottom part of common space and pump-out main line, and it can communicate with central part of common space. Circulator with oil receiver is installed in common space to communicates its bottom part with additional nozzles. To lubricate second support in proposed oil system, space of second support communicates with common space by breathing main line, and additional nozzles arranged in said space communicate with bottom part of common space through ejector.
 Two-shaft gas-turbine engine / 2250386
Proposed gas-turbine engine includes low-pressure compressor with load-bearing intermediate casing and high-pressure compressor with swivel inlet guide apparatus and rotor mounted on bearing on side of first impeller of high-pressure compressor. Provided at outlet of intermediate casing on its bush is taper surface directed towards flow section of high-pressure compressor, thus forming slotted cavity with front baffle plate of ring of internal inlet guide apparatus of high-pressure compressor; this slotted cavity is connected with oil cavity and intermediate inlet cavity at outlet through inter-labyrinth cavity and labyrinth seals. Angle of generatrix of cone of taper surface of bush of load-bearing intermediate casing ranges from 10 to 40 deg. Ratio of height of blade of swivel inlet guide apparatus of high-pressure compressor to height of slotted cavity between taper surface of bush of load-bearing intermediate casing and baffle plate of inner ring of swivel guide apparatus of high-pressure compressor is equal to 30-70.
 Gas-turbine rotor oil support venting system / 2256810
Invention relates to lubrication of supports of gas-turbine engines. Proposed gas-turbine engine rotor oil support venting system including oil pump and venting main line communicating with oil support space and connected with breather is furnished, according to invention, with pump to out air-oil mixture. Inlet of pump is placed in communication with oil space of support, and outlet communicates with venting main line with ejection of air-oil mixture from support oil space. Said pump have common drive.
 Turbine of gas-turbine engine / 2261350
Proposed turbine of gas-turbine engine is made with support of roller bearing and cooled working blades of first and second stages whose inner spaces are connected with compressor output through intermediate spaces by pipes. Support of roller bearing is provided with inclined wall to which S-shaped flexible flange with cylindrical and radial walls is butt pointed to form circular closed space connected at input by pipes with compressor intermediate stage and at output, with inner space of second working blade. Inclined branch pipes are installed in circular space to connect inner of first working blade with compressor output by pipes. Branch pipes are installed telescopically relative to pipes and inclined wall of support.
 Gas-turbine engine inter-rotor support / 2265742
Invention relates to gas-turbine engine of aircraft and ground application, particularly to supports with bearing arranged between two rotating rotors. Support of two-shaft gas-turbine engine contains bearing installed between shafts of low-pressure and high-pressure rotors, oil space separated from air spaces by seals and provided with oil feed holes made on shafts of low-and high-pressure rotors. Space is formed on inner surface of shaft of high-pressure rotor. Said space is limited by beads from end faces and is connected through holes with ring groove made on inner surface of shaft of high-pressure rotor. Oil feed channels pass from ring groove to both sides, being connected with side ring grooves located in area of end faces of bearing inner race. Oil feed channels are turned to longitudinal axis of shaft at angle of 60-70 degrees for one row, and 110-120 degrees for other row. Vertices of angles formed by intersection of longitudinal axes of channels are pointed to side of rotation of rotor. Through holes are made in inner race of bearing at angle of 40-50 degrees to longitudinal axis of bearing. Oil-feed channels can be made of equal height. Oil feed channels of one row can be displaced circumferentially relative to other row. End faces of nuts locking inner and outer races of bearing can be installed in direct contact with end faces of bearing races. Seals separating oil space from air spaces can be made of graphite, and end faces of nuts locking graphite seals are installed directly in contact with elements of graphite seals. Proposed bearing cooling system improves temperature condition of bearing, reduces axial temperature irregularities of inner and outer races of bearings. Reduced pack of parts decreases runout at tightening of bearing and seals.
 Turbine rotor support of high-temperature gas-turbine engine / 2267018
According to invention, inner housing of support is made in form of three-layer envelope which forms, in addition to oil space, cooling air ring space enclosing oil space, also discharge air ring space. Load-bearing posts are rigidly connected with all three layers of inner housing envelope. Spaces of posts communicate with cooling air space and, through metering holes, with space formed between fairing, outer housing and inner housing with load-bearing posts. Pre-oil spaces communicate with discharge air ring space. Fairing consists of sectors installed for free thermal expansion.
 Method of venting oil space of gas-turbine engine rotor support / 2267625
Invention relates to lubrication of rotor supports of gas-turbine engine, particularly, to methods of venting of rotor support oil spaces. According to proposed method including oil supply into oil space of rotor support and draw out of air-oil mixture into mixture into breather along venting main line, additional oil is delivered into oil space of rotor support and is directed to inlet of venting main line. Amount of additional oil is not less than 1% of amount of oil delivered into rotor support for lubrication and cooling of friction parts and units.
 Oil system of gas-turbine engine / 2267626
Invention relates to devices used for delivery of oil bearings of rotors of gas-turbine drives of power-generating plants. Design peculiarity of gas-turbine plan with free turbine used for driving power generators is long-time rotation of rotor of said turbine exceeding 20-30 min after switching off engine gas generator. To provided lubrication of free turbine rotor bearings in process of runout, hydraulic accumulator is included into processed oil system. Said hydraulic accumulator is connected in parallel with oil feed line from pressure set into operation from rotor of gas generator to nozzles of free turbine bearings. Space of set is filled with oil from feed main line of oil system. Oil delivery to bearings is provided at operating duties by-passing hydraulic accumulator. Supply of metered out amount of oil to turbine bearings after switching off of engine is provided owing to hydrostatic head. For this purpose device is arranged higher than level of oil space of free turbine, and jet is installed in channel connecting device with nozzles of said turbine to limit delivery of oil. Such manner of connection of hydraulic accumulator into oil system of gas-turbine engine provides lubrication of bearings of said turbine in process of long-time runout of rotor at compact design of device.
 Twin-engine aircraft oil tank / 2267627
Proposed oil tank of two-engine aircraft is made of two chambers arranged at different sides relative to vertical symmetry plane of engine and communicating through oil and air spaces. One of chambers consists of two compartments with common air space. Oil intake for delivery pump is arranged in one compartment, and other compartment is connected in its lower part with pipeline connecting oil spaces of chambers. At least one channel communicates said compartments in their lower parts.
 Discharge system for gas-turbine journal bearings / 2269666
Proposed system specially designed to raise turbine speed of rotation and to keep desired proportion between temperature and pressure within gas turbine is used for gas-turbine supporting members or bearings, in particular for second journal bearing and has central shaft with a number of journal bearing shells around it which, in their turn, are joined with casing for shells; it also has sleeve for second journal bearing of turbine and a number of pipes, respectively, for feeding and discharging lubricating and cooling oil; in addition, system has a number of side seals disposed so that they are facing second journal bearing which sets up pressure drop affording oil flow under pressure to drain tubes at constant speed.
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FIELD: motors and pumps. SUBSTANCE: oil system of power gas turbine unit (PGTU) relates to motor building, namely to PGTU oil systems, used in gas pumping and electric stations for driving of various units (pumps, gas and air compressors, electric generators etc.). The proposed PGTU is featured by the use of independent drainage vessels for each oily cavity of free turbine, connected to the individual scavenge pump, that allows to exclude in the oil scavenge system disbalance in operation of the pumps induced by moves of air flows from one oil cavity to another one through the integrated drainage cavity. EFFECT: invention will allow to avoid the use of complementary extraction pump with electric drive, and mutual integration of pump mains of delivery pumps in the oil supply system will allow to improve the reliability of PGTU operation in case of failure of one of delivery pumps. 2 cl, 1 dwg
The invention relates to the field of engine development, in particular, to the oil system gas turbine power plant (AGTU) used on gas and electric power stations to drive a variety of equipment (pumps, gas and air compressors, generators). Known oil system gas turbine power plant comprising devices for feeding and pumping oil from the oil cavity of the supporting bearings of the rotor of the turbocharger and a free turbine. Device for pumping oil from the oil cavity free turbine includes a drain tank provided with suction highways pumps driven by the turbocharger, and the highway venting through a normally open shutoff valve (see RF patent №2277175, IPC F02C 7/06, publ. 27.05.2006,). In a famous oil system device for pumping oil from the oil bearing cavities of the power turbine rotor contains a single drainage capacity for both oil cavities and additional suction pump with electric drive, which are involved in the work when it is full. When working power plant air pressure in the oil bearing cavities of the rotor of the power turbine varies significantly due to various leaks in them through the air seal. The result is e air has the ability through a single drain tank to flow from the oil cavity of the support bearing, where its pressure is higher in the oil cavity of the other support bearing where the pressure is lower, leading to disruption of the pumps running on malovostochnaja emulsion and originally designed for a specific stock performance. Disruption pumps will overflow drainage capacity and the need to include additional suction pump with an electric drive, which reduces the reliability of the oil system AGTU. The separation between the mains supply oil in the oil cavity of the bearing supports the rotor of the turbocharger and power turbine is not possible in case of failure of one of the delivery pumps, for example the pumping of pump power turbines with electric drive, to ensure the supply of oil in it from another delivery pump driven by a turbocharger that reduces the reliability of the power plant oil system. The objective of the invention is to prevent a malfunction of pumps by eliminating the flow of air flows between the oil cavity of the supporting bearings of the rotor of the turbocharger and a free turbine. This task is solved in that the oil system gas turbine power plant comprising devices for feeding and pumping Mac is and from the oil cavity of the supporting bearings of the rotor of the turbocharger and a free turbine, moreover, the device for pumping oil from the oil cavity free turbine includes a drain tank provided with suction highways pumps driven by the turbocharger, and the highway venting through a normally open shut-off valve according to the invention the drain tank is made in the form of two isolated from each other cavities, each of which is communicated with an oil cavity only one of the bearing supports of the free turbine and connected to one of the pumps, equipped with a separate line venting connected to the input of the stop valve, and the oil supply device pressure line intake pumps turbocharger and a free turbine connected together. In addition, a separate line of venting cavities drain vessel equipped with nozzles and connected in parallel to a common shut-off valve. The use of Autonomous sump tanks for each of the oil cavity of the bearing support of the rotor of the free turbine can virtually eliminate peredachku air flow from a single oil cavity to another, because the contamination of air by superwomen highways can be neglected (the flow area highways venting drain tank two orders of magnitude smaller bore suction mA is Estrela pumps). The invention prevents imbalance in the operation of pumps free turbine and eliminates the overflow drainage capacity that will allow to refuse the use of the device for pumping oil from the oil cavity free turbine from additional suction pump with an electric drive. The Association between a pressure of highways delivery pumps turbocharger and a free turbine will prevent the breakage energy installation in case of failure of any of the delivery pumps (power turbine or turbocharger), as it allows to ensure mesopotania turbocharger and a free turbine, albeit with a low pressure oil supply (within permissible limits). Oil system AGTU includes expendable tank 1, the oil cavity of the bearing supports the rotor of the turbocharger and a free turbine, respectively 2, 3 and 4. On the box of the actuator 5 is driven by the rotor of the turbocharger is fitted with: a suction pump 6, a pressure pump 7 and two suction pump 8, 9, the inputs of which are connected to the bottom of the cavities 10 and 11 of the drain tank 12. Oil cavity 3 and 4 of the free turbine through a suction line 13 and 14 are communicated with the upper part of the cavities 10 and 11 of the drain tank 12. Cavity 10, 11 have an individual line Suvorova what I respectively 15 and 16, provided with nozzles 17 and 18. Highway venting 15 and 16 output combined into a single highway 19, which are connected to the input of a normally open controlled shut-off valve 20. Oil system AGTU a second delivery pump 21 with an electric drive. The pressure line 22 and 23 of the intake of the pumps 7 and 21 of the consolidated and reported through a line 24 with the cavity control of the shutoff valve 20. The command to run AGTU simultaneously incorporated in the work of forcing the pumps 7 and 21. Performance delivery pump 7 increases gradually as the promotion of the rotor of the turbocharger and the inlet of the pump 21 with the actuator starts to work instantly and mainly provides mesopotania installation in this mode. As you spin the rotor of the turbocharger and a free turbine intake pump 21 may be disconnected and mesopotania installation will be provided only forcing pump 7 driven by the rotor of the turbocharger, but when you stop AGTU can be re-enabled due to the fact that run-free turbine is greater than the run of the turbocharger, and not bearing a free turbine to leave without lubrication with continued rotation of the free turbine rotor (under the action of inertia of the drive unit). During operation of the pumping pumps 7 and 21 oil on apronym highways 22 and 23 is supplied to the nozzles of the oil cavities 2, 3 and 4, and highway 24 in the cavity control of the shutoff valve 20, which is closed, blocking the access of atmospheric air in the cavity 10 and 11 of the drain tank 12. Waste oil from the oil cavities 3, 4 free suction turbines highways 13 and 14 through isolated from each other closed cavity 10 and 11 are fed to the inlet of the suction pump 8 and 9, which can get him into the supply tank 1 for reuse. From the oil cavities 2 of the turbocharger waste oil is conveyed into the feed tank 1 suction pump 6. The presence of highways venting 15, 16 of the two nozzles 17 and 18, taking into account their low throughput, eliminates partecke air flow between the cavities 10, 11 drain tank 12, which ensures the reliable operation of pumps 8, 9. At stop AGTU decreases the oil pressure at the outlet of the intake of the pump 7, and then 21, therefore, in the cavity of the control of the shutoff valve 20 that opens, informing cavity 10 and 11 with the atmosphere and providing a drain them in the oil residue from the oil cavities 3, 4 power turbines, which are removed from the drain tank 12 through the drain valves at the subsequent maintenance AGTU. The implementation of the invention will improve the reliability of the oil system AGTU and the mouth of the unit as a whole. 1. Oil system gas turbine power plant comprising devices for feeding and pumping oil from the oil cavity of the supporting bearings of the rotor of the turbocharger and a free turbine, and a device for pumping oil from the oil cavity free turbine includes a drain tank provided with suction highways pumps driven by the turbocharger, and the highway venting through a normally open shut-off valve, characterized in that the drain tank is made in the form of two isolated from each other cavities, each of which is communicated with an oil cavity only one of the bearing supports of the free turbine and connected with one of the pumps, equipped with a separate line of venting, which is connected to the inlet shut-off valve, and the oil supply device pressure line intake pumps turbocharger and a free turbine connected. 2. Oil system the energy of a gas turbine under item 1, characterized in that a separate line of venting cavities drain vessel equipped with nozzles and connected in parallel to a common shut-off valve.
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