JP5818622B2 - Lubricating oil supply device - Google Patents

Description

  The present invention relates to a lubricating oil supply device that supplies lubricating oil to a bearing that supports a turbine shaft of a gas turbine.

Conventionally, for example, the lubricating oil supply device (bearing mechanism) described in Patent Document 1 has an object of improving maintenance and simplifying the mechanism. The lubricating oil supply device is mounted on a mother ship, flying in standby until it is fired, to wait to perform the engine start while rotating the rotor of the engine by ram pressure caused by the flight of the uterine machine from the mother ship a bearing mechanism in the engine Xiang body, wherein a bearing for rotatably supporting the rotor is lubricated by grease at the time of standby, the the engine of the flying body is started by the time of flight to flight emitted from the mother machine, from the compressor Oil mist generating means for generating oil mist for lubricating the bearing using compressed air.

  Conventionally, for example, the lubricating oil supply device (lubricating device) described in Patent Document 2 can continue the operation of the engine even when one of the conventional elements of the device fails and an oil pressure loss occurs. It aims to work passively. The lubrication oil supply device is a lubrication device for an element that requires lubrication in a normal operation mode and an abnormal operation mode, and receives a lubricant in a normal operation mode and contains a reserve amount of lubricant. And an aspirator that is in communication with a reserve amount of lubricant and that is directly and continuously driven by pressurized fluid extracted from the fluid flow path of the turbine engine in both modes of operation.

JP 2001-165390 A Japanese Patent No. 413997

  The above-described conventional lubricating oil supply device uses a high-pressure fluid extracted from a compressor of a turbine engine, sucks the lubricating oil stored in the tank by this high-pressure fluid, and supplies it to the bearing as an oil mist. It is possible to suppress an increase in size and weight and to reduce manufacturing costs. However, in the conventional lubricating oil supply apparatus, since the high-pressure fluid is at a high temperature, there is a possibility that the bearing is overheated and the rotation function of the bearing is lowered, so that a cooling means is required. The lubricating oil supply device described in Patent Document 2 cools the high pressure fluid by penetrating a pipe through which the high pressure fluid passes into the lubricating oil tank before the high pressure fluid and the lubricating oil are mixed. Since the medium for heat exchange of the high-pressure fluid is lubricating oil, the lubricating oil is heated, and as a result, the bearing cooling effect is small.

  The present invention solves the above-described problems, and an object thereof is to provide a lubricating oil supply device that can lubricate and cool a bearing while suppressing an increase in size and weight.

In order to achieve the above-mentioned object, a lubricating oil supply device according to the present invention is a lubricating oil supply device that supplies lubricating oil to a bearing that rotatably supports a turbine shaft of a gas turbine. An air supply pipe whose other end is arranged toward the bearing, and an other end that is connected to the compressor of the gas turbine and penetrates into the air supply pipe is arranged toward the bearing side, and in the middle One end of the bleed pipe provided with a throttle portion and the other end of the bleed pipe connected to the lubricating oil tank in which lubricating oil is stored and penetrated into the inside of the bleed pipe are on one end side of the bleed pipe And a lubricating oil pipe disposed on the surface.

  According to this lubricating oil supply device, when the gas turbine is operated, the high-pressure working fluid compressed by the compressor is guided to the bearing side in the supply pipe through the extraction pipe by the pressure reduction by the throttle unit. It is burned. For this reason, in an air supply pipe, one end side becomes low pressure and external air is sucked and supplied toward the bearing. At the same time, inside the air supply pipe, the lubricating oil is sucked into the air supply pipe from the other end of the lubricating oil pipe and mixed with the suction of the outside air to be supplied as oil mist to the bearing. According to this lubricating oil supply device, the working fluid compressed by the compressor has a high temperature, but the working fluid and the lubricating oil are cooled by the outside air. Moreover, since the high-pressure working fluid compressed by the compressor is guided to the air supply pipe, the outside air and the lubricating oil are sucked through the air supply pipe, so that a pump for feeding the lubricating oil is not required. Further, since the working fluid and the lubricating oil are cooled by the outside air, a heat exchanger for cooling the lubricating oil is not required. As a result, the bearing can be lubricated and cooled while suppressing an increase in size and weight of the gas turbine.

  Moreover, the lubricating oil supply apparatus of the present invention is characterized in that a venturi portion is formed in a portion of the air supply pipe between the other end of the extraction pipe and the other end of the lubricating oil pipe.

  According to this lubricating oil supply device, since the pressure on the bearing side is reduced from the other end of the lubricating oil pipe inside the air supply pipe by the venturi section, the differential pressure with the high-pressure working fluid becomes larger. Oil can be efficiently sucked into the air supply pipe, and oil mist can be efficiently supplied to the bearing.

Moreover, the lubricating oil supply device of the present invention is applied to a flying gas turbine engine.

In a flying gas turbine engine, grease lubrication is often applied to lubricate a bearing. However, if grease is lost due to flying for a longer time, the bearing cannot be lubricated.
Therefore, oil mist can be supplied to lubricate the bearings, but installing a pump that sends the lubricant and a heat exchanger for cooling the lubricant will increase the size and weight of the flying object. It is not preferable because it invites. In this regard, according to the lubricating oil supply device of the present invention, it is possible to supply oil mist to the bearing while suppressing an increase in size and weight of the gas turbine and to cool the bearing. Therefore, a more remarkable effect can be obtained with respect to flying of the flying object for a long time.

  According to the present invention, the bearing can be lubricated and cooled while suppressing an increase in size and an increase in weight.

FIG. 1 is a schematic diagram of a lubricating oil supply apparatus according to an embodiment of the present invention. FIG. 2 is an enlarged view of the lubricating oil supply apparatus shown in FIG.

  Embodiments according to the present invention will be described below in detail with reference to the drawings. Note that the present invention is not limited to the embodiments. In addition, constituent elements in the following embodiments include those that can be easily replaced by those skilled in the art or those that are substantially the same.

  FIG. 1 is a schematic view of a lubricating oil supply apparatus according to the present embodiment, and FIG. 2 is an enlarged view of the lubricating oil supply apparatus shown in FIG. The lubricating oil supply device of the present embodiment supplies lubricating oil to a bearing 52 that rotatably supports a turbine shaft 51 in a gas turbine 50.

  As illustrated in FIG. 1, the gas turbine 50 includes a compressor 53, a combustor 54, and a turbine 55.

  The turbine shaft 51 is rotatably supported by a bearing 52 with respect to the casing 50 a of the gas turbine 50. A plurality of bearings 52 are provided in the longitudinal direction along the central axis S of the turbine shaft 51 (two are shown in FIG. 1).

  The compressor 53 includes an impeller 531 and a diffuser 532, and the impeller 531 and the diffuser 532 are accommodated in the casing 50a. The impeller 531 includes a disk 531a and a plurality of blades 531b arranged radially around the disk 531a. The disk 531 a is attached to the turbine shaft 51, whereby the impeller 531 rotates around the central axis S in the same direction together with the turbine shaft 51. The casing 50a forms a flow path 533 through which a working fluid (for example, air) passes. The flow path 533 is formed in an annular shape with the central axis S as the center, and from the front edge side of the blade 531b, which is the smaller diameter side of the disk 531a of the impeller 531, while passing between the blades 531b, radially outward of the disk 531a. It reaches the rear edge side of the blade 531b which is the large diameter side. The diffuser 532 is provided on the downstream side of the impeller 531 in the flow path 533 formed by the casing 50 a, and has a plurality of vanes between opposing wall surfaces of the flow path 533, and the blade 531 b is rotated by the rotation of the impeller 531. The kinetic energy of the passing working fluid is converted into pressure energy.

  The combustor 54 is formed by a casing 50 a and includes a main pressure chamber 541 and a combustor chamber 542. The main pressure chamber 541 is formed in an annular shape around the central axis S, and is connected to the downstream side of the flow path 533 of the compressor 53 to guide the working fluid to the combustor chamber 542. The combustor chamber 542 is formed in an annular shape around the central axis S, is provided through the main pressure chamber 541, is provided with a fuel nozzle 543, and is formed through the turbine 55.

  The turbine 55 includes a disk 55a and a plurality of turbine blades 55b arranged on the outer periphery of the disk 55a. The disk 55a is attached to the turbine shaft 51, whereby the turbine 55 rotates in the same direction around the central axis S together with the turbine shaft 51. Further, the turbine 55 is covered with a turbine nozzle 551 formed by the casing 50a.

In such a gas turbine 50, when the impeller 531 rotates around the central axis S in the compressor 53, the working fluid is guided to the main pressure chamber 541 while being compressed, and enters the combustor 54. After being mixed with the fuel supplied by the fuel nozzle 543 in the combustor 54 and burned, it is led to the turbine 55 as a high-temperature combustion gas, and the turbine shaft 51 is rotated around the central axis S together with the turbine 55. Thereafter, the combustion gas is discharged from the turbine nozzle 551. The gas turbine 50 is applied as a flying body engine, for example.

  As shown in FIGS. 1 and 2, the lubricating oil supply apparatus 1 of the present embodiment that supplies lubricating oil to the bearing 52 of the gas turbine 50 described above includes an air supply pipe 2, an extraction pipe 3, and a lubricating oil pipe. 4. As shown in FIG. 1, the lubricating oil supply device 1 is provided for each of a plurality of bearings 52. When a plurality of bearings 52 are accommodated in one bearing accommodating portion (not shown) formed of the casing 50a, one lubricating oil supply device 1 is provided corresponding to the bearing accommodating portion. May be.

The air supply pipe 2 is attached to the casing 50a, one end 2a is opened to the outside air, and the other end 2b is disposed toward the bearing 52 (or bearing housing portion). That is, the air supply pipe 2 forms a passage through the outside of the casing 50a ( flying body ) and the portion where the bearing 52 is disposed.

  The bleed pipe 3 is attached to the casing 50 a, one end 3 a is connected to the high pressure side (the rear stage of the diffuser 532) in the compressor 53 of the gas turbine 50, and the other end 3 b is inserted into the air supply pipe 2. . The other end 3b penetrated into the air supply pipe 2 is arranged toward the bearing 52 side. That is, the bleed pipe 3 forms a passage through which the high pressure side of the compressor 53 and the inside of the air supply pipe 2 are passed. Further, the extraction pipe 3 is provided with a throttle portion 3c in the middle thereof. The throttle portion 3c is formed by an orifice or an on-off valve. When the throttle 3c is an on-off valve, the on-off valve is adjusted so that the middle of the extraction pipe 3 is throttled. further. The extraction pipe 3 is formed with a choke 3d in which the other end 3b penetrating into the supply pipe 2 is narrowed.

  The lubricating oil pipe 4 has one end 4 a connected to a lubricating oil tank 5 in which lubricating oil is stored, and the other end 4 b penetrating into the air supply pipe 2. The other end 4 b penetrating into the air supply pipe 2 is disposed closer to the one end 2 a of the air supply pipe 2 than the extraction pipe 3. That is, the lubricating oil pipe 4 forms a passage through which the lubricating oil tank 5 and the inside of the air supply pipe 2 are passed.

  As described above, the lubricating oil supply apparatus 1 according to the present embodiment includes the supply pipe 2 in which the one end 2 a is opened to the outside air and the other end 2 b is disposed toward the bearing 52, and the one end 3 a in the compressor 53 of the gas turbine 50. Is connected to the inside of the air supply pipe 2 and the other end 3b is arranged toward the bearing 52, and the extraction pipe 3 is provided with a throttle portion 3c on the way, and the lubricating oil tank 5 in which lubricating oil is stored. The other end 4 b connected to one end 4 a and penetrating into the air supply pipe 2 is provided with the lubricating oil pipe 4 disposed on the one end 2 a side of the air supply pipe 2 with respect to the bleed pipe 3.

  In the lubricating oil supply device 1, when the gas turbine 50 is operated, the high-pressure working fluid compressed by the compressor 53 passes through the bleed pipe 3 by the pressure reduction by the throttle portion 3c, and the bearing 52 is provided inside the supply pipe 2. Guided to the side. For this reason, in the air supply pipe 2, the one end 2 a side becomes a low pressure and the outside air is sucked and supplied toward the bearing 52. At the same time, inside the air supply pipe 2, the lubricating oil is sucked into the air supply pipe 2 from the other end 4 b of the lubricating oil pipe 4, mixed with the suction of outside air, and supplied to the bearing 52 as oil mist.

  Thus, in the lubricating oil supply apparatus 1 of the present embodiment, the working fluid compressed by the compressor 53 is at a high temperature, but the working fluid and the lubricating oil are cooled by the outside air. Moreover, the lubricating oil supply apparatus 1 of the present embodiment sucks the outside air and the lubricating oil through the air supply pipe 2 when the high-pressure working fluid compressed by the compressor 53 is guided to the air supply pipe 2. Does not require a pump to send oil. Moreover, since the lubricating oil supply apparatus 1 of this Embodiment cools a working fluid and lubricating oil with external air, the heat exchanger for cooling lubricating oil is not required. As a result, it is possible to lubricate and cool the bearing 52 while suppressing an increase in size and weight of the gas turbine 50.

  In addition, since the choke 3d is formed on the other end 3b of the bleed pipe 3, the flow rate of the working fluid toward the bearing 52 in the air supply pipe 2 becomes faster, so that the outside air and the lubricating oil are efficiently supplied to the air supply pipe. 2 can be sucked into the interior.

  The lubricating oil tank 5 is formed of a material (for example, a synthetic resin material having flexibility) that contracts when the lubricating oil is sucked, or a contracting portion (for example, A bellows structure). In addition, the lubricating oil tank 5 may be provided with a suction port (or a suction pipe) so as to suck in air outside the tank as the lubricating oil is sucked. The suction port (or suction pipe) is provided with a check valve so that the lubricating oil does not leak.

  Further, in the lubricating oil supply device 1 according to the present embodiment, the venturi portion 2c is formed at the site of the air supply pipe 2 between the other end 3b of the extraction pipe 3 and the other end 4b of the lubricating oil pipe 4. Is preferred.

  According to this lubricating oil supply device 1, since the pressure on the bearing 52 side is reduced from the other end 4b of the lubricating oil pipe 4 inside the air supply pipe 2 by the venturi portion 2c, the differential pressure with the high-pressure working fluid is larger. Therefore, the outside air and the lubricating oil can be efficiently sucked into the air supply pipe 2, and the oil mist can be efficiently supplied to the bearing 52.

Moreover, it is preferable that the lubricating oil supply apparatus 1 of this Embodiment is applied in a flying gas turbine engine.

In the flying gas turbine engine, grease lubrication is often applied when the bearing 52 is lubricated. However, when the grease is lost due to flying for a longer time, the bearing 52 cannot be lubricated. Therefore, it is sufficient to supply the oil mist to lubricate the bearing 52. However, the provision of a pump for sending the lubricating oil and a heat exchanger for cooling the lubricating oil increases the size and weight of the flying object. This is not preferable. In this regard, according to the lubricating oil supply device 1 of the present embodiment, it is possible to supply oil mist to the bearing 52 while suppressing an increase in size and weight of the gas turbine 50, and the bearing 52 is cooled. Therefore, it becomes possible to obtain a more remarkable effect against the flying of the flying object for a long time. In the flying object , when lubricating oil is supplied to the bearing 52, grease lubrication may be performed together with the supply of the oil mist of the present embodiment.

  In order to efficiently supply the lubricating oil to the bearing 52, it is preferable that a plurality of the lubricating oil supply devices 1 of the present embodiment be provided along the direction around the bearing 52. In this case, a plurality of air supply pipes 2 are provided, and the extraction pipes 3 and the lubricating oil pipes 4 branched from the respective air supply pipes 2 are inserted.

DESCRIPTION OF SYMBOLS 1 Lubricating oil supply apparatus 2 Supply pipe 2a One end 2b Other end 2c Venturi part 3 Extraction pipe 3a One end 3b Other end 3c Restriction part 3d Choke 4 Lubricating oil pipe 4a One end 4b Other end 5 Lubricating oil tank 50 Gas turbine 51 Turbine shaft 52 Bearing 53 Compressor 54 Combustor 55 Turbine

Claims (3)

In a lubricating oil supply apparatus that supplies lubricating oil to a bearing that rotatably supports a turbine shaft of a gas turbine,
An air supply pipe having one end open to the outside air and the other end facing the bearing;
A bleed pipe having one end connected to the compressor of the gas turbine and the other end penetrating into the interior of the air supply pipe disposed toward the bearing side, and a throttle portion provided in the middle;
A lubricating oil pipe having one end connected to a lubricating oil tank in which lubricating oil is stored and the other end penetrating into the air supply pipe disposed closer to one end of the air supply pipe than the other end of the extraction pipe;
A lubricating oil supply device comprising:   The lubricating oil supply device according to claim 1, wherein a venturi portion is formed at a portion of the air supply pipe between the other end of the extraction pipe and the other end of the lubricating oil pipe. The lubricating oil supply device according to claim 1, wherein the lubricating oil supply device is applied to a flying gas turbine engine.

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