US3267671A

US3267671A - Turbine engine

Info

Publication number: US3267671A
Application number: US469798A
Authority: US
Inventors: Charles L Hill
Original assignee: Individual
Current assignee: Individual
Priority date: 1965-07-06
Filing date: 1965-07-06
Publication date: 1966-08-23
Anticipated expiration: 1983-08-23

Description

C. L. HILL TURBINE ENGINE Aug. 23, 1966 2 Sheets-Sheet 1 Filed July 6, 1965 INVENTOR. CHARLES L..HILL

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ATTORNEY 3, 1966 c.1 HILL 3,267,671

TURBINE ENGINE Filed July 6, 1965 2 Sheets-Sheet 2 FIGA 73 72 1 FIG.6

I I J.

INVENTOR. CHARLES L.HILL BY i wimzi' dq ATTORNEY United States Patent 3,267,671 TURBINE ENGINE Charles L. Hill, 111 Foster St., Olney, Ill. Filed July 6, 1965, Ser. No. 469,798 13 Claims. (El. 60-39.43)

The present invention relates to a continuous combustion gas turbine engine.

Continuous combustion gas turbine engines of the multistage axial flow type are well known. Although these engines have been extremely satisfactory for the purposes intended, they are nevertheless relatively expensive due to the use of the many turbine and compressor blades which must be carefully machined and assembled. For low power applications where the blade tolerances would be extremely critical, the well known types of axial flow gas turbine engines are not generally considered to be economically feasible.

It is a principal object of the present invention to pro vide a new and improved type of gas tunbine engine that will be particularly economical to manufacture for low and medium size power use.

Another object of the present invention is to provide an improved type of gas turbine engine with extremely simple forms of turbine rotor and compressor elements together with a simple form of valving arrangement that may be easily manufactured and assembled in economical form for either low or medium power applications.

Yet another object of the present invention is to provide an improved form of gas turbine engine that does not use either turbine blades or compressor blades.

A feature of the invention according to a basic embodiment thereof is the provision of a turbine casing having rotatably mounted therein a turbine rotor. The turbine rotor is provided with peripheral pockets against which the forces of momentum of the expanding gaseous products of combustion are directed to :power the rotation of the rotor. lobes is rotatably positioned in the casing with its lobes adapted to engage the pockets of the turbine rotor as the rotor and valve wheel rotate. Also provided in like number to the number of valve wheels is at least one compressor wheel having peripheral lobes and rotatably positioned in the casing with its lobes adapted to engage the turbine rotor as the rotor and compressor wheel rotate. Each compressor wheel is positioned at a point spaced from each valve wheel in the direction of rotation of the turbine rotor. An air intake passage through said casing is provided near the junction of each valve wheel and the rotor where their lobes and pockets disengage and a compressed air outlet passage is provided through the casing near the junction of each compressor wheel and the rotor where their lobes and pockets engage. The compressed air passage is connected to a combustion chamber by means of which air compressed between the pockets and lobes by the rotation of the rotor and compressor wheel is injected into the combustion chamber. Suitable means to inject fuel into the combustion chamber is also provided together with ignition means to ignite the gaseous fuel mixture of compressed air and fuel. Passage means for the expanding gaseous products of combustion from the combustion chamber is provided to convey such expanding gases into the turbine casing against the rotor pockets at a point spaced from the position of the compressor wheel along the direction of rotation of the rotor between each compressor wheel and each valve wheel. An exhaust passage is provided near the junction of each valve wheel and the rotor Where their lobes and pockets engage to provide for the exhaust of-expanding :gases leaving the turbine pockets as the turbine rotor rotates.

At least one valve wheel having peripheral Another feature and advantage of the turbine engine arrangement of the invention is the manner in which it may be modified to provide increased power without requiring a proportionate complication of parts. For example, one modified embodiment may provide a plural like number of valve wheels, compressor wheels and combustion chambers spaced uniformly around the periphery of a single turbine rotor in the predetermined order of valve wheel, compressor wheel and combustion chamber in the direction of rotation of said rotor. Another modified embodiment of the invention would provide that a plural number of turbine rotors be spaced axially on a common shaft with each rotor having its own valve wheels, compressor wheels and combustion chambers as required.

Further objects, features and attendant advantages of the invention will be apparent with reference to the following specification and drawings, in which:

FIGURE 1 is a more or less diagrammatic sectional plan view of one embodiment of the turbine engine of the invention;

FIGURE 2 is a side elevational view of the engine shown by FIGURE 1;

FIGURE 3 is a top plan view similar to FIGURES 1 and 2;

FIGURE 4 is a fragmentary side elevational view of a modified form of the engine;

FIGURE 5 is a top plan diagrammatic view of yet another embodiment of the invention; and

FIGURE 6 is a side elevational view of the embodiment of FIGURE 5.

Referring now to FIGURES 13 of the drawings, a first embodiment of the invention will now be described in detail. The turbine engine is compresed of a casing having front and back wall 10 and 11 and suitable side walls which are variously shaped and will be referred to in detail in the following description. It will be understood by those skilled in the art that the shape and construction of the turbine casing is only diagrammatically shown for the sake of simplicity of the drawings and that the front and back walls are dimensioned to closely fit the planar surfaces of the turbine rotor 12, the valve wheel 13 and the compressor wheel 14 in a manner to restrict gas flow as is well known in the art. The turbine rotor 12 is carried by a shaft 15 that is rotatably journaled in the front and back walls 10, 11 of the casing in any suitable manner (not shown), it also being understood that suitable gas seals for the journal bearings of the shaft 15 are provided as is well known to those skilled in the art. Similarly, the valve wheel 13 is carried by a shaft 16 and the compressor wheel 14 is carried by a shaft 17, both of which are also rotatably journaled in the front and back walls 10, 11 of the casing by suitable bearings and seals not shown in detail.

The turbine rotor 12 is provided with a plurality of peripheral pockets such as shown at 2%! and each of the valve and

compressor wheels

13, 14 respectively is provided with a plurality of peripheral lobes such as shown at 21, 22. In the preferred arrangement, the lobes such as shown at 21, 22 are complementary in shape to the turbine pockets such as shown at 20 and the positions of the valve and

compressor wheels

13, 14 are such that the lobes of the wheels engage in meshing relation with the pockets of the turbine rotor so as to cause rotation of the wheels in one direction as the turbine rotor revolves in the opposite direction. In order to minimize wear on the lobes and pockets, the gears 23-25 may be secured to the respective shafts 1517 to cause the rotor 12 and

wheels

13, 14 to rotate in synchronism although it will be understood that the engine wouldbe operative without using the gears 23-25 since the meshing of the pockets a and lobes is similar to a gear drive. When using the gears 2325 it is not necessary that the

lobes

21, 22 be exactly complementary in shape to the pockets of the turbine although for maximum compressor efiiciency, as will be described, complementary shapes for the pockets and lobes are believed to be preferred.

An air intake passage 30 is provided through a side wall of the casing near the point of junction or position 31 between the valve wheel 13 and the turbine rotor 12 where their lobes 21 and pockets disengage assuming that the rotor is driven counterclockwise in the direction of the arrow and the valve wheel is driven clockwise. Instead of the intake passage any suitable opening (not shown) through the back or front walls of the casing in the vicinity of the position 31 may be provided for air intake in a similar manner to the compressed air passages or

openings

32, 33 which are provided through the front and back casing walls it}, 11. The

compressed air openings

32, 33 are located at positions spaced from the position 31 along the direction of rotation of the rotor 12 at the junction of the compressor wheel 14 and the rotor 13 where their lobes and pockets meet so that the air compressed between the lobes and pockets as they engage is expelled through the

compressed air pipes

34, 35 t0 the combustion chamber 36. Although two

compressed air passages

34, 35 and corresponding

openings

32, 33 are described, it should be understood that only a single opening 33 and connecting passage 35 may be required.

Fuel is injected into the combustion chamber 36 by any suitable nozzle means 37 and ignition means 38 is also provided to ignite the initial charge of fuel and compressed air gaseous mixture as is well known in the art. The expanding gaseous products of combustion from the combustion chamber 36 are directed through the outlet passage 39 into the turbine casing against a turbine rotor pocket such as shown at 20 and the momentum and expansion forces of the products of combustion acting against the pocket 20 cause the turbine rotor iii to be powered for rotation. An exhaust passage 40 is provided in the casing near the postion 4d at the junction of the valve wheel 21 and rotor d2 where their lobes and pockets engage and the engaging movement of the lobes of the valve wheel '33 with the pockets of the rotor 12 provide a desirable positive pressure and scavenging action for the exhaust gases. i

It will be noted that the pontions of the casing side wall between the valve wheel 13 and compressor wheel 14 along the direction of rotation of the rotor are dimensioned to tit closely as shown at 42 in gas restricting or I sealing relation to the periphery of the rotor 12. Also, the side walls of the casing around the valve wheel 13 and the compressor wheel 14 tit closely to the peripheries of such wheels in gas restricting or sealing relation as shown at 43, 4-4. It may be desirable, although it is not required for a functional tunbine, to provide auxiliary air intake openings through the casing such as shown at 45 where the lobes of the compressor wheel 14 disengage with the pockets of the rotor 12 to create a suction. A-ir thus 'drawn in will be carried with the lobe 22 of the compressor wheel 14 to the compressed air openings 32:33 for injection into the combustion chamber 36. The side wall of the casing at 46 also fits closely in gas restricting or sealing relation to the periphery of the rotor 12 so as to separate the expanding gaseous products of combustion from the auxiliary air intake opening 45.

:Reviewing now the operation of the gas turbine engine described above in connection with FIGURES 1-3 of the drawings, it will be understood that as the rotor rotates in the counterclockwise direction, the disengagement of the lobes of the valve wheel 13 with the pockets of the rotor 12 will create a suction to draw air through the air intake 30 to be carried with the turbine rotor pockets to be compressed between the engaging lobes of the compressor wheel 14 and the pockets of the rotor 12. to be expelled through the compressed air passages 34, 3S and injected into the combustion chamber 36. There the compressed air is mixed with injected fuel and ignited to form expanding gaseous products of combustion which are directed against the turbine rotor pockets to cause powered rotation of the turbine rotor. It should be understood that the direction of rotation for the rotor :12 and compressor 'wheel 14 at the start of combustion is as shown by the arrow so that the expanding gaseous products of combustion are not drawn into the

compressed air passages

34, 35 but are expelled through passage '39 against the rotor peripheral pocket 20 due to the relative mechanical advantages presenting resistance to the forces of the expanding gases in the combustion chamber.

Referring now to FIGURE 4 of the drawings, a modified form of the invention is shown in which two turbine casings having respective front and

back walls

60, 61, and

62, 63 similar to the walls described at 10, 11 for PIG- URES 1-3 are provided. Each turbine casing contains a rotor secured to a common shaft 64 and valve rwheel secured to the commonshaft 65 together with a compressor wheel secured to the common shaft 66, the shafts 6446 being interconnected by gearing 67-69. The arrangement of each rotor and associated valve and compressor wheels is the same as previously described in connection with FIGURES l-3 of the drawings. Thus a multiple rotor form of turbine engine with the rotors spaced axially along a common drive or rotor shaft is provided and it will be obvious that any number of casing and rotor assemblies may be spaced axially along a common rotor shaft.

Referring now to FIGURES 5 and 6 of the drawings,

yet another modified form of invention in which a single rotor is operated with a multiple number of combustion chambers, valve wheels and compressor wheels. For example, a first valve wheel is positioned in the casing at 70 with the air intake shown at 71, a compressor wheel at 72, a combustion chamber at 73 and an exhaust passage at 74 adjacent a second valve wheel at 75. Similarly in like order there is provided the air intake 76,

the compressor wheel 77, the combustion chamber 78 and the exhaust passage '79 adjacent the first valve wheel at 70. Gears (not shown) may be provided to interconnect the rotor shaft 80 and the various compressor and valve wheel shafts 81-84- to minimize wear on the rotor pockets and the lobes of the valve and compressor Wheels as previously described. Obviously, depending on the relative sizes of the turbine rotor and the valve and compressor wheels, any number of combustion chambers and associated valve and compressor wheels may be spaced around the periphery of the rotor in the described order of valve wheel, compressor wheel, and combustion chamber along the direction of rotation of the rotor.

Various modifications will occur to those skilled in the art. For example, the exhaust gases may be redirected against other peripheral portions of the turbine rotor or may be directed to another rotor of a tandem turbine unit. The particular shapes for the pockets, lobes and passageways are not limited to those diagrammatically shown and described since many variations will occur to those skilled in the art and may be desirable for desired conditions of operation such as may be determined by the exercise of engineering skill.

What is claimed is:

l. A gas turbine engine comprising a casing, a turbine I rotor journaled in said casing and having a plurality of peripheral pockets, a valve wheel having a plurality of peripheral lobes and rotatably journaled in said casing at a first position with its lobes adapted to engage the pockets of said rotor as said rotor and valve wheel are rotated, a compressor wheel having a plurality of peripheral lobes and rotatably journaled in said casing with its lobes adapted to engage the pockets of said rotor as said wheel and rotor are rotated at a second position spaced along the direction of rotation of said rotor from the first position of said valve wheel, an air intake passage through said casing adjacent the position of said valve wheel and said rotor where their lobes and pockets disengage, an exhaust passage through said casing adjacent the position of said valve wheel and said rotor where their lobes and pockets engage, a compressed air passage through said casing adjacent the position of said compressor wheel and said rotor Where their lobes and pockets engage, a combustion chamber, means to inject fuel into said chamber, means connecting said air passage to said chamber to inject compressed air into said chamber to form a gaseous mixture with the injected fuel, means to ignite the gaseous mixture in said chamber, passage means to convey expanding gaseous products of combustion from said chamber into said casing against the periphery of said rotor at a third position spaced from the position of said compressor wheel along the direction of rotation of said rotor, and

means to convey exhaust gases in said casing from said L third position to said exhaust passage, the side walls of said casing fitting closely in gas restricting relation around said valve and compressor wheels, the side walls of said casing fitting closely in gas restricting relation around said rotor between said valve wheel and said compressor wheel from said intake passage to said compressed air passage and between said third position and said compressor wheel.

2. A gas turbine engine comprising a casing, a turbine rotor journaled in said casing and having a plurality of peripheral pockets, a valve wheel having a plurality of peripheral lobes of complementary shape to the pockets of said rotor and rotatably journaled in said casing at a first position with its lobes adapted to engage the pockets of said rotor as said rotor and valve wheel are rotated, a compressor wheel having a plurality of peripheral lobes of complementary shape to the pockets of said rotor and rotatably journaled in said casing with its lobes adapted to engage the pockets of said rotor as said wheel and rotor are rotated at a second position spaced along the direction of rotation of said rotor from the first position of said valve wheel, an air intake passage through said casing adjacent the position of said valve wheel and said rotor where their lobes and pockets disengage, an exhaust passage through said casing adjacent the position of said valve Wheel and said rotor where their lobes and pockets engage, a compressed air passage through said casing adjacent the position of said compressor wheel and said rotor where their lobes and pockets engage, a combustion chamber, means to inject fuel into said chamber, means connecting said air passage to said chamber to inject compressed air into said chamber to form a gaseous mixture with the injected fuel, means to ignite the gaseous mixture in said chamber, passage means to convey expanding gaseous products of combustion from said chamber into said casing against the periphery of said rotor at a third position spaced from the position of said compressor wheel along the direction of rotation of said rotor, and means to convey exhaust gases in said casing from said third position to said exhaust passage, the side Walls of said casing fitting closely in gas restricting relation around said valve and compressor wheels, the side walls of said casing fitting closely in gas restricting relation around said rotor between said valve wheel and said compressor wheel from said intake passage to said compressed air passage and between said third position and said compressor wheel.

3. A gas turbine engine comprising a casing, a turbine rotor journaled in said casing and having a plurality of peripheral pockets, a valve wheel having a plurality of peripheral lobes and rotatably journaled in said casing at a first position with its lobes adapted to engage the pockets of said rotor as said rotor and valve wheel are rotated, a compressor wheel having a plurality of peripheral lobes and rotatably journaled in said casing with its lobes adapted to engage the pockets of said rotor as said wheel and rotor are rotated at a second position spaced along the direction of rotation of said rotor from the first position of said valve wheel, gear means interconnecting said rotor with said valve and compressor wheels to cause said rotor and wheels to rotate in synchronism, an air intake passage through said casing adjacent the position of said valve wheel and said rotor where their lobes and pockets disengage, an exhaust passage through said casing adjacent the position of said valve wheel and said rotor where their lobes and pockets engage, a compressed air passage through said casing adjacent the position of said compressor wheel and said rotor where their lobes and pockets engage, a combustion chamber, means to inject fuel into said chamber, means connecting said air passage to said chamber to inject compressed air into said chamber to form a gaseous mixture with the injected fuel, means to ignite the gaseous mixture in said chamber, passage means to convey expanding gaseous products of combustion from said chamber into said casing against the periphery of said rotor at a third position spaced from the position of said compressor wheel along the direction of rotation of said rotor, and means to convey exhaust gases in said casing from said third position to said exhaust passage, the side walls of said casing fitting closely in gas restricting relation around said valve and compressor wheels, the side walls of said casing fitting closely in gas restricting relation around said rotor between said valve wheel and said compressor wheel from said intake passage to said compressed air passage and between said third position and said compressor wheel.

4. A gas turbine engine comprising a casing, a turbine rotor journaled in said casing and having a plurality of peripheral pockets, a valve wheel having a plurality of peripheral lobes of complementary shape to the pockets of said rotor and rotatably journaled in said casing at a first position with its lobes adapted to engage the pockets of said rotor as said rotor and valve wheel are rotated, a compressor wheel having a plurality of peripheral lobes of complementary shape to the pockets of said rotor and rotatably journaled in said casing with its lobes adapted to engage the pockets of said rotor as said wheel and rotor are rotated at a second position spaced along the direction of rotation of said rotor from the first position of said valve wheel, gear means interconnecting said rotor with said valve and compressor wheels to cause said rotor and wheels to rotate in synchronism, an air intake passage through said casing adjacent the position of said valve wheel and said rotor where their lobes and pockets disengage, an exhaust passage through said casing adjacent the position of said valve wheel and said rotor where their lobes and pockets engage, a compressed air passage through said casing adjacent the position of said compressor wheel and said rotor where their lobes and pockets engage, a combustion chamber, means to inject fuel into said chamber, means connecting said air passage to said chamber to inject compressed air into said chamber to form a gaseous mixture with the injected fuel, means to ignite the gaseous mixture in said chamber, passage means to convey expanding gaseous products of combustion from said chamber into said casing against the periphery of said rotor at a third position spaced from the position of said compressor wheel along the direction of rotation of said rotor, and means to convey exhaust gases in said casing from said third position to said exhaust passage, the side walls of said casing fitting closely in gas restricting relation around said valve and compressor wheels, the side walls of said casing fitting closely in gas restricting relation around said rotor between said valve wheel and said compressor wheel from said intake passage to said compressed air passage and between said third position and said compressor wheel.

5. A gas turbine engine comprising a casing, a turbine rotor journaled in said casing and having a plurality of peripheral pockets, a valve wheel having a plurality of peripheral lobes and rotatably journaled in said casing at a first position with its lobes adapted to engage the pockets of said rotor as said rotor and valve wheel are rotated, a compressor wheel having a plurality of peripheral lobes and rotatably journaled in said casing with its lobes adapted to engage the pockets of said rotor as said wheel and rotor are rotated at a second position spaced long the direction of rotation of said rotor from the first position of said valve wheel, an air intake passage through said casing adjacent the position of said valve wheel and said rotor where their lobes and pockets disengage, an auxiliary air intake passage through said casing adjacent the position of said compressor wheel and said rotor where their lobes and pockets engage, an exhaust passage through said casing adjacent the position of said valve wheel and said rotor where their lobes and pockets engage, a compressed air passage through said casing adjacent the position of said compressor wheel and said rotor Where their lobes and pockets engage, a combustion chamber, means to inject fuel into said chamber, means connecting said air passage to said chamber to inject compressed air into said chamber to form a gaseous mixture with the injected fuel, means to ignite the gaseous mixture in said chamber, passage means to convey expanding gaseous products of combustion from said chamber into said casing against the periphery of said rotor at a third position spaced from the position of said compressor Wheel along the direction of rotation of said rotor, and means to convey exhaust gases in said casing from said third position to said exhaust passage, the side walls of said casing fitting closely in gas restricting relation around said valve and compressor wheels, the side walls of said casing fitting closely in gas restricting relation around said rotor between said valve wheel and said compressor Wheel from said intake passage to said compressed air passage and between said third position and said compressor wheel.

6. The invention of claim 1 in which said turbine engine is comprised of a like plural number of rotors, valve wheels, compressor wheels and combustion chambers spaced axially, with the rotors connected to a common shaft for concurrent rotation.

7. The invention of claim as in which gear means is provided to interconnect the common shaft and said wheels for synchronous rotation of said rotors and wheels.

8. The invention of claim 1 in which a like plural number of valve wheels, compressor wheels and combustion chambers are positioned around the rotors in the order stated in relation to the direction of rotation of the rotor.

9. The invention of claim 8 in which gear means is provided to interconnect the common shaft and said wheels for synchronous rotation of said rotor and wheels.

it). The invention of claim 1 in which there are a plural number of rotors spaced axially and a like plural number of valve wheels, compressor wheels and combustion chambers positioned around each rotor in the order stated in relation to the direction of rotation of each rotor, with the rotors connected to a respective common shaft for concurrent rotation.

11. The invention of claim it) in which gear means is provided to interconnect the common shaft and said rotors and wheels for synchronous rotation of said rotors and Wheels.

12. The invention of claim 1 in which there are a plural number of rotors spaced axially and a like plural number of valve wheels, compressor wheels and combustion chambers positioned around each rotor in the order stated in relation to the direction of rotation of each rotor, with the rotors connected to a respective common shaft for concurrent rotation and with like ones of the wheels for each rotor being connected by common shafts for concurrent rotation.

13. The invention of claim 12 in which gear means is provided to interconnect all of the common shafts for synchronous rotation.

References Cited by the Examiner UNITED STATES PATENTS 2,349,600 5/1944 Adams 60--39.45

3,233,406 2/1966 Holt 6039.43

MARK NEWMAN, Primary Examiner. R. D. BLAKESLEE, Assistant Examiner.

Claims

1. A GAS TURBINE ENGINE COMPRISING A CASING, A TURBINE ROTOR JOURNALED IN SAID CASING AND HAVING A PLURALITY OF PERIPHERAL POCKETS, A VALVE WHEEL HAVING A PLURALITY OF PERIPHERAL LOBES AND ROTATABLY JOURNALED IN SAID CASING AT A FIRST POSITION WITH ITS LOBES ADAPTED TO ENGAGE THE POCKETS OF SAID ROTOR AS SAID ROTOR AND VALVE WHEEL ARE ROTATED, A COMPRESSOR WHEEL HAVING A PLURALITY OF PERIPHERAL LOBES AND ROTATABLY JOURNALED IN SAID CASING WITH ITS LOBES ADAPTED TO ENGAGE THE POCKETS OF SAID ROTOR AS SAID WHEEL AND ROTOR ARE ROTATED AT A SECOND POSITION SPACED ALONG THE DIRECTION OF ROTATION OF SAID ROTOR FROM THE FIRST POSITION OF SAID VALVE WHEEL, AN AIR INTAKE PASSAGE THROUGH SAID CASING ADJACENT THE POSITION OF SAID VALVE WHEEL AND SAID ROTOR WHERE THEIR LOBES AND POCKETS DISENGAGE, AN EXHAUST PASSAGE THROUGH SAID CASING ADJACENT THE POSITION OF SAID VALVE WHEEL AND SAID ROTOR WHERE THEIR LOBES AND POCKETS ENGAGE, A COMPRESSED AIR PASSAGE THROUGH SAID CASING ADJACENT THE POSITION OF SAID COMPRESSOR WHEEL AND SAID ROTOR WHERE THEIR LOBES AND POCKETS ENGAGE, A COMBUSTION CHAMBER, MEANS TO INJECT FUEL INTO SAID CHAMBER, MEANS CONNECTING SAID AIR PASSAGE TO SAID CHAMBER TO INJECT COMPRESSED AIR INTO SAID CHAMBER TO FORM A GASEOUS MIXTURE WITH THE INJECTED FUEL, MEANS TO IGNITE THE GASEOUS MIXTURE IN SAID CHAMBER, PASSAGE MEANS TO CONVEY EXPANDING GASEOUS PRODUCTS OF COMBUSTION FROM SAID CHAMBER INTO SAID CASING AGAINST THE PERIPHERY OF SAID ROTOR AT A THIRD POSITION SPACED FROM THE POSITION OF SAID COMPRESSOR WHEEL ALONG THE DIRECTION OF ROTATION OF SAID ROTOR, AND MEANS TO CONVEY EXHAUST GASES IN SAID CASING FROM SAID THIRD POSITION TO SAID EXHAUST PASSSAGE, THE SIDE WALLS OF SAID CASING FITTING CLOSELY IN GAS RESTRICTING RELATION AROUND SAID VALVE AND COMPRESSOR WHEELS, THE SIDE WALLS OF SAID CASING FITTING CLOSELY IN GAS RESTRICTING RELATION AROUND SAID ROTOR BETWEEN SAID VALVE WHEEL AND SAID COMPRESSOR WHEEL FROM SAID INTAKE PASSAGE TO SAID COMPRESSED AIR PASSAGE AND BETWEEN SAID THIRD POSITION AND SAID COMPRESSOR WHEEL.