JPS60162020A - Thrust controller for exhaust turbine supercharger - Google Patents

Abstract

PURPOSE:To minimize the pressure-receiving area of each thrust bearing despite the reactionary force of a turbine, by controlling the thrust acting on the back of the impeller of a compressor, and those acting on both the sides of a turbine disk, to eliminate or minimize the thrust of a rotor shaft. CONSTITUTION:An enclosed chamber A on the compressor side of a turbine disk 12 and an air discharge port 37 are connected to each other through a high- pressure air introducing pipe 46 furnished with a control valve 45. An enclosed chamber B and an exhaust gas outlet port 40 are connected to each other through an exhaust gas communication pipe 48 furnished with a control valve 47. An enclosed chamber C is connected to an atmosphere release pipe 44 furnished with a control valve 43. The output signals of the temperature transmitter 49, which transmits the temperatures of a thrust bearing 23 near a compressor and a thrust bearing 24 near a turbine, and those of a valve opening degree transmitter 50, which transmits the degree of opening of the control valves 43, 45, 47, are entered into an opening degree discriminator 51 connected to an actuator 54 through a deviation corrector 52 and a control unit 53.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a shaft thrust adjustment device for an exhaust turbine supercharger in which a rotor shaft is supported between an exhaust turbine and a compressor.

A conventional structure of an exhaust turbine supercharger in which a rotor shaft is supported between an exhaust turbine and a compressor is shown in FIG. That is, the compressor impeller 1 which takes in air from the air suction port 36 of the compressor casing 35 and discharges compressed air from the air discharge port 37 and the gas population 39 of the turbine casing 38 are also rotated by the flowing exhaust gas. A rotor shaft 13 connects a turbine disk 12 with a protruding turbine blade 11 for discharging exhaust gas that has finished its work from an exhaust gas outlet 40, and the compressor side of the intermediate portion of the rotor shaft is connected to the compressor side. With journal bearing 21,
The turbine side is supported by a turbine side journal bearing 22, and compressor side thrust bearings 23 are installed on the compressor side on both sides of the thrust receiver 41, which is protruded from the rotor shaft 13 at the intermediate portion between the two bearings. A turbine-side thrust bearing 24 is disposed on each side to support the axial thrust, and a compressor-side labyrinth packing 25 and a turbine-side labyrinth packing 26 are installed on both sides of the journal bearings to prevent lubricating oil. In addition to preventing leakage, an air leakage prevention labyrinth packing 29 is provided around the outer periphery of the sealed chamber (C) on the back of the impeller to release the air in the sealed chamber to the atmosphere through the air release path 42. Sealed chambers (A) and (B) are arranged on both sides of the turbine disk, and the sealed chamber (A) is sealed by a labyrinth packing 27 for preventing leakage of high-pressure air arranged on the outer periphery of the disk. High-pressure air from the air outlet can be freely introduced into the sealed chamber through a high-pressure air path 31 bored in the bearing case 30 in which the bearing is housed, or through a conduit, and the sealed chamber (B) is provided with high-pressure air. An exhaust gas intrusion prevention labyrinth packing 28 disposed on the outer periphery of the disk prevents gas from entering, and the chamber is communicated with the atmosphere or connected to the gas outlet passage via a pipe.

Note that the exhaust gas from the exhaust gas inlet is passed through the nozzle 33o.
'The inflow of the turbine blade IJ from the nozzle population 32 and the exhaust gas outlet are made up of a gas outlet casing 34.

Therefore, when considering the axial thrust of the above-mentioned structure of the conventional exhaust turbine supercharger, for convenience of explanation, the axial thrust is divided into the compressor side and the turpino side.
If the direction of the axial thrust is positive (+) from the turbine side to the compressor side, then the thrust force FB on the compressor side is
The force FBI from the air suction port 36 side of the impeller 1 and the back side,
In other words, it is the sum of the force FB2 from the closed chamber (C) side, but since the force FB2 is large, it is always in the positive (+) direction, and its value is extremely small for a compressor with a high pressure ratio, so it is the sum of the force FB2 from the closed chamber (C) side.
C) Internal air is released to the atmosphere to reduce thrust FB. In addition, the thrust force FT on the turbine side is the resultant force FT1 of the pressure difference before and after the turbine blades and the momentum (always in the positive (+) direction, but its magnitude depends on the degree of reaction of the turbine), the closed chamber (A , ) side FT2 (approximately determined by the compressor discharge pressure Pd and acts in the negative (-) direction)
, and the force F”ra from the closed chamber (B) side (the force F
Like TI, it is influenced by the degree of reaction of the turbine, and is positive (
Therefore, the axial thrust FTo'r is the resultant force of the compressor side thrust FB and the turbine side thrust FT. and will change depending on the degree of reaction of the turbine. Now, if the change in the degree of reaction of the turbine in the axial thrust F"roT is shown in Figure 2, if the degree of reaction of the turbine is large, the axial thrust FTOT will be It is known that it becomes a large force in the positive (+) direction, and when the degree of recoil is small, it becomes a force in the negative (-) direction. For this reason, in the conventional exhaust turbine supercharger, the pressure receiving area difference between the compressor-side thrust bearing 23 and the turbine-side thrust bearing 24 is adjusted to correspond to the magnitude of the axial thrust FToT that changes according to changes in the degree of reaction of the turbine. However, these structures are not only unsatisfactory in terms of performance, but also have problems in terms of manufacturing cost structure. This is also a bad idea.

This invention was made in view of the current situation, and by making it possible to adjust the thrust force acting on the back surface of the compressor impeller and the thrust force acting on both sides of the rotor disk, the rotor shaft can be adjusted. To provide a axial thrust adjustment device for an exhaust turbine supercharger, which makes the axial thrust zero value and minimum value, and satisfies the pressure receiving area of each thrust bearing with the minimum value regardless of the degree of reaction of the turbine. The purpose is to

Next, an embodiment of the present invention will be described with reference to the drawings.
In FIG. 3, the air inlet 3 of the compressor casing 35
The compressor impeller 1 and the turbine casing 38 are rotated by the flow gas from the exhaust gas population 39 of the turbine casing 38, and the gas that has finished its work is transferred to the gas outlet. Exhaust gas outlet 4 of casing 34
A turbine blade 11 for discharging air from 0 is connected to a protruding turbine disk 12 through a rotor shaft 13 having a thrust bearing 41 disposed in the middle, and compressor-side journal bearings 21 are connected to both sides of the intermediate portion of the rotor shaft. and turbine-side journal bearings 22, and the compressor-side thrust bearings 23 and turbine-side thrust bearings 24 support the axial thrust on both sides of the thrust bearings. A labyrinth packing 25 on the compressor side and a labyrinth packing 26 on the turbine side are installed to prevent lubricating oil leakage, and the back of the impeller is sealed in a closed chamber (C
), and a sealed chamber (A) is formed by a high-pressure air leakage prevention labyrinth packing 27 having the compressor side of the turbine disk on its outer periphery, and an exhaust gas intrusion prevention labyrinth packing 27 having the opposite side of the compressor on its outer periphery. At 28, sealed chambers (B) are respectively formed, and atmospheric discharge pipes 44 with ml control valves (■c) 43 are connected to appropriate locations of the sealed chambers (C) of the exhaust turbine supercharger to release the atmosphere. The closed chamber (A) and the air outlet are connected by a high pressure air introduction pipe 46 through a control valve (VA) 45, and the closed chamber (B) and the gas An exhaust gas communication pipe 48 is connected to the outlet casing via a control valve (VB) 47.
A temperature transmitter 4 transmits the temperature of the compressor side thrust bearing 23 and the turbine side thrust bearing 11 + bearing 24.
9 and control valves (VA) 45, (VB) 47, (VC
)43 The valve opening transmitter 50 transmits the valve opening of each of the control valves so that the temperature difference detected by receiving the temperature of the side thrust bearing is always within a certain range. It is connected to an opening degree determination device 51 that calculates and gives instructions according to a preset process, and then corrects the deviation between the valve opening degree detection value of each control valve and the valve opening degree setting value given by the opening degree determination device. The deviation corrector 52 is further sent to a valve opening controller 53 which sets an increase/decrease in the valve opening in accordance with the opening deviation value corrected by the corrector. It is connected continuously to an actuator 54 that transmits an increase/decrease in the valve opening degree to each valve.

Therefore, according to the present invention, since the pressure in each sealed chamber can be controlled by adjusting the valve opening degree of each of the control valves, it is possible to control the individual thrust and the axial thrust of the entire supercharger. , this is 4th a, 4th, 4th, 4th, 4th,
4 Force, 4 Ki, and 4 Diagram To explain using an example of adjusting the axial thrust (not shown in the diagram), the resultant force FTI of the pressure difference before and after the turbine blade and the motion force is determined by the degree of reaction of the turbine in Figure 4A. I'11 (reaction Keio University) to T21 (reaction degree small)
The force FT from the closed chamber (A) side is uniquely determined within the range of
2, in FIG. 4A, the control valve (VA) 45 can be controlled to adjust the range from T21 (when the control valve is fully open) to T22 (when the control valve is fully open), so the intermediate T
24 settings can be made, and 1 is the force FTi from the closed chamber (B) side.
In Figure 4, when the control valve (VB) is fully closed, l+ is uniquely determined in the range from T3□ (reaction level, before adjustment) to Ta2 (reaction level is small, before adjustment). , (1) The pressure PB in the sealed chamber (B) is set to the gas outlet pressure P.
The valve is closed when E or less (PB≦PE), and PB>P
(2) Since the gas flow from the sealed chamber toward the gas outlet is restricted by the gas intrusion prevention labyrinth packing 28, an orifice of an appropriate shape is used instead of the valve (VB). Or, if you install the above function and can perform any of the uncontrolled functions, the force F
A constant force T33 (control valve (
Therefore, as shown in the fourth engineering drawing, the thrust force FT on the turbine side can be adjusted to T by the control adjustment of the control valves (VA) and (VB).
43 (Reaction Keidai, FT adjusted to the minimum possible, T48 ”
Ti□10T2□10T33) to T44 (low recoil, FT
20 W ~ adjustment, T442 T12 + T2. Next, the force FB from the air suction port of the compressor impeller is uniquely determined as 13th according to the compressor specifications in Figure 4. The power of FE2
can be adjusted in the range of B2□ (when the valve is fully closed) to B22 (when the valve is fully open) by controlling the control valve (VC) in the fourth force diagram, so settings such as 828, 824 etc. Therefore, the thrust force FB on the compressor side is
In Fig. 4, by adjusting the control valve (VC), B4, (when the valve is fully closed, J34, = B11 + B
21) to B42 (when the valve is fully open) B42-Btt
+B22), so it can be set within the range of 84
3 (B48 = B2O+ 828), B44 (1
344=Btt+B24), etc. can be freely set. As mentioned above, since the thrust force FT1 on the turbine side and the thrust force FB on the compressor side can be set by controlling the respective control valves, the axial thrust force FT of the supercharger which is the resultant force of these
OT can be set freely, and to give an example of a case where the degree of reaction is large, in the fourth diagram, when the turbine side thrust FT is positive (+) as in T48, the compressor side thrust As FB, the absolute value is equal to the above T4B,
And if thrust B411 in the opposite direction, that is, in the negative (-) direction, is selected, the axial thrust FToT becomes FTOT4B (FT
OT4g ” T43 + B2O), and the turbine side thrust FT can be adjusted to zero by itself like T44, except in cases where the degree of reaction is large, but the compressor Since the side thrust FB is naturally adjusted to a zero value like B44, the resultant force is the axial thrust FT.
It becomes 6T44 and becomes a zero value.

As described above, the present invention controls the thrust on the turbine side through the control valves (VA) and (VB), and controls the thrust on the compressor side through the control valve (VC), thereby generating the resultant force of the side thrust. Since the feeder shaft thrust can be freely controlled, its industrial value is extremely high.

[Brief explanation of the drawing]

Fig. 1 is a longitudinal cross-sectional side view of the main parts of a conventional exhaust turbine supercharger, Fig. 2 is a curve diagram showing the value of the supercharger axial thrust corresponding to the degree of reaction of the turbine, and Fig. 3 is a diagram of the present invention. 4A, 4A, 4, and 4 engineering drawings are a curve diagram showing an example of adjusting the thrust on the turbine side. The 4o, 4ka and 4ki diagrams are
The fourth diagram is a curve diagram showing an example of adjusting the compressor side thrust. The fourth diagram is a curve diagram showing an example of adjusting the supercharger axial thrust. 1... Compressor impeller, 11... Turbine blade, 12... Turbine tire, 13... Rotor shaft, 21... Compressor side journal bearing, 22... Turbine side journal bearing,
23...Compressor side thrust bearing, 24...Turbine side thrust bearing, 25...Compressor side labyrinth packing, 26...Turbine side labyrinth packing, 27...High pressure air leak prevention labyrinth packing, 28...Exhaust gas intrusion Preventing labyrinth packing, 2911・Air leak prevention labyrinth packing, 30・Bearing case, 31・High pressure air path, 3
2... Nozzle inlet, 33... Nozzle, 34... Gas outlet casing, 35... Compressor casing, 36... Air suction port, 37... Air discharge port, 38-- Turbine casing, 39... Exhaust gas Inlet, 40...exhaust gas outlet,
41... Thrust receiver, 42... Air release path, 43... Control valve (Vo), 44... Atmospheric release officer, 45... Control valve (VA
), 46... High pressure air introduction 1, 47... Control valve (VB
), 48...Exhaust gas communication pipe, 49...Temperature transmitter, 5
0... Valve opening degree transmitter, 51... Opening degree determination device, 52...
Deviation corrector, 53... Valve opening controller, 54... Actuator, (A)... Sealed chamber, (B)... Sealed chamber,
(C)...Closed room. Figure 8←Reaction 4ノ((、〕1＼】RIi: Movement 17: Fire-+Tarpin “Reaction force and procedural amendment (method) May 21, 1980 Commissioner of the Patent Office Kazu Wakasugi Mr. Husband 1. Indication of the incident: Patent Application No. 17120 of 1982 2. Title of the invention: Shaft thrust adjustment device in exhaust turbine supercharger 3.
Person making the amendment Relationship to the case Applicant Name Mitsubishi Heavy Industries, Ltd. 4, Sub-Agent Address: 8-chome, Yurakucho, Chiyoda-ku, Tokyo 100
No. 1 Hibiya Park Building No. 519 (Telephone 213-
0686) 5. Date of amendment order: April 24, 1982
Day 6, Subject of correction Drawing 7, Contents of correction Figures 4-7 and 4-3 are attached as attached, and Figure 4-A figure pressure 141!・o Exhumation pressure Pd (mtr + H$) 4th -
Fig. 4-1 RI 'JI 4- O Fig. pressure m*n Evacuation pressure ρd (mTrLH'J,) 4th-Internal cause

Claims (1)

[Claims] A turbine disk with a compressor impeller and turbine blades protruding from both ends of the shaft is arranged.A thrust receiver protruding from the middle of the rotor shaft is provided with thrust bearings on both sides, and journal bearings on both sides. At the same time, the sealed chamber on the back of the impeller is vented to the atmosphere by interposing a control valve,
Further, the sealed chamber on the compressor side of the disk and the compressor air discharge port are communicated via a control valve, and the sealed chamber on the opposite side of the disk to the compressor and the gas outlet are communicated via a control valve, respectively. A process of setting the valve opening so that the temperature difference between the side thrust bearings is always within a certain range using a temperature transmitter that transmits the temperature of the side thrust bearing and a valve opening transmitter that transmits the valve opening of each control valve. is connected to an opening degree determination device that instructs calculation according to It was connected continuously to a valve opening controller that sets the increase/decrease in the valve opening in response to the deviation value, and further to an actuator that transmits the increase/decrease in the opening of each valve to each valve based on a signal from the controller. A axial thrust adjustment device for an exhaust turbine supercharger, characterized in that: