RU2645784C1 - Three-zone multi-blade rotary internal combustion engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to the field of rotary internal combustion engines with split cycle. Invention essence lies in that compression chamber, where air is absorbed into engine, engine working chamber, where combustion gases energy is converted into rotor rotation, and chamber where fuel mixture is ignited is separated and has independent volumes and is located in different parts of engine. Combustion gases flow from the fuel chamber into working chambers through rotor body and come out under pressure from nozzles located in rotor wings. For one shaft revolution, represented engine carries out a number of operating cycles equal to number of blades forming expansion chambers.

EFFECT: technical result consists in higher engine efficiency.

8 cl, 33 dwg

Description

The invention relates to engine building, namely to rotary internal combustion engines, and can be used as a drive in various machines, stationary and mobile power plants in the automotive, tractor, electric power and other industries related to the manufacture and operation of various vehicles and power installations.

The invention provides a rotary engine device, the internal space of which is divided into the following independent areas (zones):

• the compression area in which the fuel mixture is sucked in and in which the fuel mixture is compressed,

• the area in which the ignition chamber is located, where the ignition of the fuel mixture occurs,

• the expansion area (working chamber), where the combustion fuel expands and the energy of the gases is converted into mechanical work, into which gases from the combustion chamber flow through the rotor body.

A multi-vane rotor passes through the internal space of the engine so that the engine ignition chamber is located inside the rotor shaft, which, in turn, is located along the central axis of the cylindrical engine casing and enters the compression and expansion areas of the engine, so that the rotor rotates around a stationary ignition chamber.

The engine housing in the expansion (contraction) region (zone) includes valves that, when retracted with the rotor blades, form working chambers in which the expansion of combustion gases of the fuel mixture takes place in the expansion, compression and suction regions of the fuel mixture, respectively, in the compression and ignition regions.

Thus, when the rotor rotates in the engine, the following processes occur:

• expansion chambers are created in the expansion area, where the energy of the combustion gases is converted into mechanical work,

• compression chambers are created in the compression area, where the fuel mixture is sucked in and compressed,

• compressed fuel mixture is pumped into the ignition chamber.

The number of rotor blades entering the expansion area is even.

The number of valves entering the expansion and compression region is equal to the number of rotor blades entering the expansion region.

The number of rotor blades entering the compression region is less than the number of rotor blades entering the expansion region by half.

Numerous rotary internal combustion engines are known in which the intake of a combustible mixture, its compression and combustion takes place in the working chamber, which leads to an eccentric rotation of the rotor around the shaft (Wankel engine), which is generally recognized to lead to numerous shortcomings of such engines, or to ensure planetary rotation the rotor has to move the combustion chamber, where the fuel mixture squeezed by the rotor in the rotor working chamber is squeezed out and where the mixture is ignited, beyond the side of the working chamber of the engine in which t rotation of the rotor (patents RU 2161708, RU 2163678), which in turn leads to a decrease in the characteristics of the mixture, a decrease in compression in the combustion chamber and, as a consequence, to power losses, which are significant disadvantages of these engines.

In all existing rotary engines, the process of converting the energy of combustion gases into mechanical work (expansion cycle), the suction and compression of the fuel mixture occur in the working chamber, therefore, the useful expansion cycle accounts for only part of the rotor's stroke in the working chamber, which leads to incomplete use of energy combustion gases and exhaust gases from the engine under sufficiently high pressure.

In the invention presented here, the region in which the working chambers are created in which the energy of the combustion gases is converted into rotor rotation, and the region in which the chambers are created in which air is sucked in and the fuel mixture is compressed, and the region in which the fuel mixture is ignited are divided.

Accordingly, the volumes of these cameras are independent.

Thus, in the expansion cycle, a volume is used that does not depend on the volumes where the preparation and ignition of the combustible mixture takes place, which allows it to be large enough to receive exhaust gases at the level of atmospheric pressure and, therefore, fully use the energy of the combustion gases .

In addition, the fuel combustion gases in the engine of the circuit proposed here flow from the chamber in which the fuel mixture is ignited into the working chambers through the rotor body and exit under pressure from nozzles located in the rotor wings, therefore, together with the pressure of the combustion gases on the rotor wings the reactive force emanating from them acts under the pressure of the combustion gases, which will increase the engine power.

The multi-vane rotary engine presented here will carry out the number of operating cycles equal to the number of blades creating expansion chambers per shaft revolution.

If the blades are 2, then in one revolution of the shaft the engine will perform two duty cycles (two half-cycles).

If the blades are 4, then in one revolution of the shaft the engine will perform four duty cycles (four quarter cycles), 6-6, 8-8, and so on.

Obviously, such a scheme of the engine allows to obtain greater efficiency and power than that of existing systems, with lower fuel consumption.

In FIG. 1 shows a general diagram of a two-blade engine and the ratio of its main elements in a longitudinal section.

In FIG. 2 shows a general diagram of the engine housing and the ratio of its main elements in a longitudinal section.

In FIG. 3 shows a cross section of the ignition chamber along the line bc.

In FIG. 4 shows a cross-section of the ignition chamber along the line g-g.

In FIG. 5 shows the cross section of the ignition chamber along the line dd.

In FIG. 6 shows a cross section of the ignition chamber along line e-e.

In FIG. 7 shows a general diagram of the rotor of a two-blade engine and the ratio of its main elements in a longitudinal section.

In FIG. 8 is a cross-sectional view of a two-bladed engine along line aa, showing a general diagram and the ratio of the main engine elements in the expansion area at the beginning of the duty cycle (zero point).

In FIG. 9 is a cross-sectional view of a two-blade engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression area at the beginning of the duty cycle (zero point).

In FIG. 10 is a cross-sectional view of a two-bladed motor housing along line aa, showing a general diagram and the ratio of the main elements of the motor housing in the expansion area.

In FIG. 11 is a cross-sectional view of a two-bladed motor housing along line b-b, showing a general diagram and the ratio of the main elements of the motor housing in the compression region.

In FIG. 12 is a cross-sectional view of a rotor of a two-bladed engine along the line e-e, showing a general diagram and a ratio of the main rotor elements included in the expansion area.

In FIG. 13. A cross-sectional view of a rotor of a two-bladed motor along the w-line is shown, showing the general scheme and the ratio of the main rotor elements included in the expansion area.

In FIG. 14 is a cross-sectional view of a rotor of a two-bladed motor along the s-z line, showing a general diagram and a ratio of the main rotor elements included in the expansion region.

In FIG. 15 is a cross-sectional view of a rotor of a two-bladed engine along the line i-i, showing the general scheme and the ratio of the main elements of the rotor.

In FIG. 16 is a cross-sectional view of a rotor of a two-bladed engine along the ith line, showing a general diagram and a ratio of the main rotor elements included in the compression region.

In FIG. 17 is a cross-sectional view of a two-bladed engine along line aa, showing a general diagram and the ratio of the main engine elements in the expansion area at the beginning of the duty cycle (zero point).

In FIG. 18 is a cross-sectional view of a two-blade engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression area at the beginning of the duty cycle (zero point).

In FIG. 19 is a cross-sectional view of a two-blade engine along line aa, showing a general diagram and the ratio of the main engine elements in the expansion region when the rotor rotates 45 °.

In FIG. 20 is a cross-sectional view of a two-bladed motor along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region when the rotor rotates 45 °.

In FIG. 21 is a cross-sectional view of a two-blade engine along line aa, showing the general layout and the ratio of the main engine elements in the expansion area when the rotor rotates 90 °.

In FIG. 22 is a cross-sectional view of a two-bladed motor along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region when the rotor rotates 90 °.

In FIG. 23 is a cross-sectional view of a two-bladed motor along line aa, showing the general layout and the ratio of the main engine elements in the expansion region when the rotor rotates 135 °.

In FIG. 24 is a cross-sectional view of a two-blade engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region when the rotor rotates 135 °.

In FIG. 25 is a cross-sectional view of a two-blade engine along line aa, showing a general diagram and the ratio of the main engine elements in the expansion region when the rotor reaches the end position of the expansion process.

In FIG. 26 is a cross-sectional view of a two-bladed engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region at the last stage of the compression process of the fuel mixture and squeezing it into the ignition chamber.

In FIG. 27 is a cross-sectional view of a two-bladed engine along line aa, showing the general layout and the ratio of the main engine elements in the expansion area when the rotor rotates 180 ° at the beginning of a new duty cycle (zero point).

In FIG. 28 is a cross-sectional view of a two-blade engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region when the rotor rotates 180 ° at the beginning of a new duty cycle (zero point).

In FIG. 29 is a cross-sectional view of a two-bladed engine, showing a general diagram and the ratio of the main engine elements when the residual gas pressure in the ignition chamber is controlled before it is filled with a new portion of the fuel mixture.

In FIG. 30 is a cross-sectional view of a four-blade engine, showing a general diagram and the ratio of the main engine elements in the expansion area at the beginning of the duty cycle (zero point).

In FIG. 31 is a cross-sectional view of a four-blade engine, showing a general diagram and the ratio of the main engine elements in the compression area at the beginning of the duty cycle (zero point).

In FIG. 32 is a cross-sectional view of a four-blade engine, showing a general diagram and the ratio of the main engine elements in the expansion area when the rotor rotates 45 °.

In FIG. 33 is a cross-sectional view of a four-blade engine showing a general diagram and the ratio of the main engine elements in the compression region when the rotor rotates 45 °.

The simplest version of a multi-blade rotary engine presented here is a two-blade rotary internal combustion engine consists of the following main parts and elements:

1 - Cylindrical engine housing.

2 - Motor rotor shaft.

3 - The cylindrical housing of the ignition chamber.

4 - Rotor blades entering the expansion area.

5 - Axial channel inside the rotor shaft, which includes the cylinder of the ignition chamber.

6 - The rotor blade (s) entering (s) in the compression area.

7 - Channels in the rotor blades included in the expansion chamber.

8 - Nozzles in the rotor blades included in the expansion chamber.

9 - Cutout in the rotor shaft in the compression area.

10 - A jumper in the engine housing, dividing its volume into the expansion and compression region.

11 - Spark plug.

12 - Gate valves expansion area.

13 - Gate of the compression area.

14 - Extension area.

15 - Compression area.

16 - The ignition area of the fuel mixture.

17 - The output hole of the rotor shaft in the front wall of the motor housing.

18 - Hole for the rotor shaft in the wall of the motor housing separating the compression and expansion zones.

19 - Cutouts in the cylindrical body of the ignition chamber in the expansion area.

20 - Cutout in a cylindrical housing of the ignition chamber in the compression area.

21 - Channel for supplying the fuel mixture.

22 - Valve for the channel for supplying the fuel mixture.

23 - Exhaust openings in the engine housing in the expansion area.

24 - Channel feed the fuel mixture.

25 - Valve for the fuel mixture supply channel.

26 - Latch compression area.

27 - Cutout in a cylindrical housing of the ignition chamber in the compression area.

28 - Cutout in a cylindrical housing of the ignition chamber to vent residual pressure from the ignition chamber before pumping a new portion of the fuel mixture into it.

29 - Channels in the rotor housing for venting the residual pressure from the ignition chamber before pumping a new portion of the fuel mixture into it.

30 - Channel in the jumper in the engine housing, dividing its volume into the expansion and compression region, through which the residual combustion gases from the combustion chamber are discharged.

The operation of the provided rotary internal combustion engine is as follows.

The phases of the half-cycle operation of a two-bladed rotary engine in the fuel chamber are shown on the sheets of figures No. 17-28 in cross sections.

In FIG. 17 is a cross-sectional view of a two-bladed engine along line aa, showing a general diagram and the ratio of the main engine elements in the expansion area at the beginning of a working half-cycle (zero point). The rotor blades included in the expansion area 4, as close as possible to the valves of the expansion area 12, retracted into the motor housing. The channels in the rotor blades included in the expansion chamber 7 are located opposite the cutouts in the cylindrical body of the ignition chamber in the expansion region 19.

In FIG. 18 is a cross-sectional view of a two-blade engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression area at the beginning of the duty cycle (zero point). The valves of the compression area 13 and 26 are retracted into the engine housing. The compression area is divided into two cameras Kc1 and Kc2. Chamber Kc2 is completely occupied by the rotor blade entering the compression region 6. The valve of the fuel mixture supply channel 25 is open, the fuel mixture is ready to enter the chamber Kc2 through the fuel channel 24. The chamber Kc1 is filled with the fuel mixture. The valve 21 is closed, the fuel mixture does not enter the chamber Kc1 through the channel 21. The cutout in the shaft of the rotor 9 is not aligned with the cutouts in the cylindrical body of the ignition chamber in the compression region 20 and 27, and therefore, the fuel mixture from the chamber Kc1 does not enter the combustion chamber 16, which is filled with compressed fuel mixture from the chamber Kc2, which entered it at previous half-cycle engine operation.

When igniting the ignition of compressed fuel revenge in the ignition chamber 16 from the candle 11, the rotor begins to rotate.

In FIG. 19 is a cross-sectional view of a two-blade engine along line aa, showing a general diagram and the ratio of the main engine elements in the expansion region when the rotor rotates 45 °. During the rotation of the rotor, expansion chambers Kr1 and Kr2 were formed, into which the combustion gases of the fuel mixture from the combustion chamber 16 enter, suitable through cutouts in the cylindrical body of the ignition chamber in the expansion region 19, into the channels combined with them in the rotor blades entering the expansion chamber 7 , and then through the nozzle 8.

In FIG. 20 is a cross-sectional view of a two-bladed motor along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region when the rotor rotates 45 °. The valve of the compression region 13 is extended. During the rotation of rotor 2, the rotor blade, which enters the compression region 6, compresses the fuel mixture in chamber Kc1 and opens up the space in chamber Kc2, where the fuel mixture is sucked from the fuel mixture supply channel 24. Valve 23 is open, valve 22 is closed, and the valve 26 is retracted. The cutout in the rotor shaft in the compression area 9 is not aligned with the cuts in the cylindrical body of the ignition chamber in the compression areas 20 and 27, and therefore, the fuel mixture from the Kc1 chamber does not enter the combustion chamber 16, in which the fuel mixture is combusted, from the Kc2 chamber received in it during the previous half-cycle of the engine.

In FIG. 21 is a cross-sectional view of a two-blade engine along line aa, showing a general diagram and the ratio of the main engine elements in the expansion region when the rotor rotates 90 °. The expansion chambers Kr1 and Kr2 into which the combustion gases of the fuel mixture enter from the combustion chamber 16, suitable through cutouts in the cylindrical body of the ignition chamber in the expansion region 19, into channels that are still combined with them in the rotor blades entering the expansion chamber 7, and then through nozzles 8, continue to expand.

In FIG. 22 is a cross-sectional view of a two-blade engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region when the rotor rotates 90 °. The valve of the compression region 13 is extended. When the rotor 2 rotates, the rotor blade entering compression region 6 continues to compress the fuel mixture in chamber Kc1 and expand the space in chamber Kc2 where the fuel mixture is sucked from the fuel mixture supply channel 24. Valve 23 is open, valve 22 is closed, valve 26 is retracted . The cutout in the rotor shaft in the compression region 9 is still not aligned with the cutouts in the cylindrical body of the ignition chamber in the compression region 20 and 27 and, therefore, the fuel mixture from the Kc1 chamber does not enter the combustion chamber 16, in which the fuel mixture is combusted from the Kc2 chamber received in the previous half-cycle engine.

In FIG. 23 is a cross-sectional view of a two-bladed motor along line aa, showing the general layout and the ratio of the main engine elements in the expansion region when the rotor rotates 135 °. The combustion gases of the fuel mixture from the combustion chamber 16 stopped flowing into the chambers Kr1 and Kr2, since the cutouts in the cylindrical body of the ignition chamber 16 in the expansion region 19 cease to be aligned with the channels in the rotor blades entering the expansion chamber 7. The chambers Kr1 and Kr2 continue expand under the influence of excess pressure in them compared with areas beyond them on the rotor blades 4.

In FIG. 24 is a cross-sectional view of a two-blade engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region when the rotor rotates 135 °. The valve of the compression region 13 is extended. When the rotor 2 rotates, the rotor blade, which enters the compression region 6, continues to compress the fuel mixture in the chamber Kc1 and expand the space in the chamber Kc2, where the fuel mixture is sucked from the fuel mixture supply channel 24. Valve 23 is open, valve 22 is closed, and the valve 26 is retracted. The cutout in the rotor shaft in the compression region 9 approaches the cutout in the cylindrical body of the ignition chamber in the compression region 27, and therefore, the compressed fuel mixture from the chamber Kc1 will soon be able to enter the combustion chamber 16, from which the residual pressure of the combustion gases is vented through the cut in the cylindrical the housing of the ignition chamber 28, one of the channels in the rotor housing 29 aligned with it at that moment, and then through the channel in the engine housing 30, as shown in FIG. 29.

In FIG. 25 is a cross-sectional view of a two-blade engine along line aa, showing a general diagram and the ratio of the main engine elements in the expansion region when the rotor reaches the end position of the expansion process. The valves of the expansion area 12 are extended and do not interfere with the movement of the rotor blades entering the expansion zone 4 by inertia. The cutouts in the cylindrical body of the ignition chamber 16 in the expansion region 19 are not aligned with the channels in the rotor blades entering the expansion chamber 7. Residual combustion gases leave the expansion region through the exhaust openings in the engine housing 23.

In FIG. 26 is a cross-sectional view of a two-bladed engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region at the last stage of the compression process of the fuel mixture and squeezing it into the ignition chamber. When the rotor 2 rotates, the rotor blade entering the compression region 6 aligns the compressed fuel mixture from the cutting chamber Kc1 to the ignition chamber 16. Chamber Kc2, where the fuel mixture is sucked from the fuel mixture supply channel 24 at the last expansion stage. The valve 23 is open, the valve 22 is closed, the valve 26 is retracted. The cutout in the rotor shaft in the compression region 9 is aligned with the cutout in the cylindrical body of the ignition chamber in the compression region 27, the compressed fuel mixture from the Kc1 chamber enters the combustion chamber 16, from which the residual pressure of the combustion gases is vented through the cutout in the cylindrical housing of the ignition chamber 28, one of the channels combined with it at this moment in the rotor housing 29, and then through the channel in the motor housing 30, as shown in FIG. 29.

In FIG. 27 is a cross-sectional view of a two-bladed engine along line aa, showing the general layout and the ratio of the main engine elements in the expansion area when the rotor reaches the half-cycle of revolution. The rotor has rotated 180 ° and is at the beginning of a new half-cycle (zero point). The rotor blades included in the expansion area 4, as close as possible to the valves of the expansion area 12, retracted into the motor housing. The channels in the rotor blades included in the expansion chamber 7 are located opposite the cutouts in the cylindrical body of the ignition chamber in the expansion region 19.

In FIG. 28 is a cross-sectional view of a two-bladed engine along line b-b, showing a general diagram and the ratio of the main engine elements in the compression region when the rotor reaches the half-cycle revolution. The rotor has rotated 180 ° and is at the beginning of a new half-cycle (zero point). The valves of the compression area 13 and 26 are retracted into the engine housing. The compression area is divided into two cameras Kc1 and Kc2. Chamber Kc1 is completely occupied by the rotor blade entering the compression region 6. The valve of the fuel mixture supply channel 22 is open, the fuel mixture is ready to enter the chamber Kc1 through the fuel channel 22. The chamber Kc2 is filled with the fuel mixture. The valve 25 is closed, the fuel mixture does not enter the Kc2 chamber through the channel 24. The cutout in the shaft of the rotor 9 is not aligned with the cutouts in the cylindrical body of the ignition chamber in the compression region 20 and 27, and therefore, the fuel mixture from the chamber Kc2 does not enter the combustion chamber 16, which is filled with compressed fuel mixture from the chamber Kc1, which entered it at previous half-cycle engine operation.

When the fuel mixture is ignited in the ignition chamber 16, the rotor will receive a new impulse to move, and the next half-cycle of its operation will begin from the position shown in FIG. 17-18.

In the case of a four-blade rotor, the engine will operate for a quarter cycle, when the engine will pass the zero point four times in one 360 ° rotation of the rotor.

In FIG. 30-33 show cross-sections of a four-blade rotary engine in the expansion region at the zero point of FIG. 30 and when the rotor rotates 45 °, FIG. 32, and in the compression region at the zero point of FIG. 31 and when the rotor rotates 45 °, FIG. 33.

Accordingly, four expansion chambers — Kr1, Kr2, Kr3, Kr4 — will be formed in the expansion region of the four-bladed motor engine, and four chambers — Kc1, Ks2, Ks3, Ks4 — two of which will be in the compression stage of the fuel mixture — in FIG. 33 Kc1 and Kc3 and two in the stage of suction of the fuel mixture - in FIG. 33 Ks2 and Ks4.

Thus, for the full circle of rotation of the rotor for a two-blade engine:

in the compression chamber occur:

• two compression cycles of the fuel mixture;

• two cycles of suction of the fuel mixture.

In the working chamber of a rotary engine occur:

• two cycles of expansion of combustion gases;

• two cycles of removal of residual combustion gases.

In the ignition chamber of a rotary engine occur:

• two cycles of suction of the fuel mixture;

• two ignition cycles of the fuel mixture;

• two cycles of venting of excess pressure of residual combustion gases.

The rotor receives rotation energy:

• from the expansion pressure of the combustion gases on the rotor blades;

• from reactive recoil of fuel combustion gases emanating under pressure from the rotor blades.

The separate position of the compression, expansion and combustion chamber of the rotary engine allows them to be dimensioned so that during the expansion of the combustion gases after they have done useful work at the outlet of the engine’s working chamber, their residual pressure can be obtained close to atmospheric, that is, to fully use the energy of expansion of the combustion gases fuel.

With an increase in the number of rotor blades and engine valves, the number of engine operating cycles proportionally increases at one revolution of the rotor.

Claims (8)

1. A multi-vane rotary internal combustion engine, consisting of: a compression region in which compression chambers are formed, an expansion region in which expansion chambers and combustion chambers, a multi-vane rotor, compression and expansion chamber valves are formed, characterized in that the compression, expansion and the ignition chamber has independent volumes and each of them is located in a separate part of the engine, the fuel mixture is sucked in and compressed in the compression chambers, enters the combustion chamber, from where the combustion gases of the fuel through the rotor body stumble into the expansion chamber where make useful work, rotating rotor. 2. The engine according to claim 1, characterized in that the ignition chamber has the shape of a cylinder and passes through the expansion and compression regions of the engine along its central axis. 3. The engine according to claim 1, characterized in that the rotor of the engine passes through the compression and expansion areas of the engine and consists of: a rotor shaft, rotor blades included in the expansion area, and rotor blades included in the compression region of the engine. 4. The engine according to claim 3 is characterized in that there is a cylindrical cutout inside the rotor in which the engine ignition chamber is located in such a way that the rotor rotates around a stationary cylindrical engine ignition chamber. 5. The engine according to claim 3, characterized in that the rotor has channels extending through the rotor body from the cylindrical cutout inside the rotor shaft, in which the engine ignition chamber is located, inside the rotor blades entering the expansion region, on the rotor shaft between the compression and expansion regions , on the shaft of the rotor included in the compression area. 6. The engine according to claim 2, characterized in that the ignition chamber has cutouts in the region of expansion of the engine, between the regions of compression and expansion, and in the region of compression. 7. The engine according to claim 4, characterized in that the rotor of the engine, rotating around the combustion chamber of the engine, is sequentially connected by channels inside the rotor blades included in the expansion zone, with cut-outs of the ignition chamber in the expansion region, by channels on the rotor shaft between the compression and expansion regions with the ignition chambers were cut between the compression and expansion regions, the channels on the rotor shaft entering the compression region, with the ignition chamber cut-outs in the compression region, so that while one connection is open, the others are closed. 8. The engine according to claim 1, characterized in that the expansion chambers in the engine expansion area are formed by the engine casing, the expansion area valves pulled into the engine casing and the rotor blades entering the expansion area, the compression chambers in the engine compression area are formed by the engine casing, retracted into the engine engine valves of the compression region and the rotor blades included in the compression region.

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