Abstract:
A gas turbine engine uses a carburetor or a fuel injector and spark ignition devices to fuel and fire it. A gear pump compresses the air/fuel mixture into a compressor discharge passage connected to ignition holes. The spark ignition devices thread into the ignition holes and ignite the combustible mixture which is pumped up through the ignition holes into horizontal combustion passages that flow the burning gas in between the turbine rotors on their downstream side. The gas pressure forces the turbine rotors in each pair of turbines to accelerate in opposite directions. The turbine rotors are located on the compressor drive shafts and drive the counter rotating compressor rotors. The combustion gas flows through the top sides of the turbines and flows out the sides of the housing through exhaust ports. Another embodiment uses a fuel injector and the combustion gas is pumped into the upstream side of the turbines.

Description:
BACKGROUND OF THE INVENTION  
       [0001]     Gas turbine engines are well known in the art and many embodiments have been patented. These include the well known aircraft jet engine which is designed to produce exhaust thrust, the turbo prop gas turbine engine designed to drive a propeller and produce exhaust thrust as commonly seen in high bypass jumbo jet applications that have greater fuel efficiency, and gas turbine engines designed to produce shaft horse power or torque commonly used to drive helicopter rotors. In each case gas turbine engines are continuous combustion machines and are generally employed as suitable aero engines. The instant invention is also designed to produce torque or shaft horse power but is primarily intended for land vehicle propulsion where wheel drive and fuel efficiency are required. This engine may also be designed to produce thrust as well as torque.  
         [0002]     These engines may be regarded as hybrid engines combining the features of internal combustion engines and gas turbine engines to produce a new type of engine suitable for a multitude of applications as ground, sea, air, and space power sources. This invention is unique in that it can use a standard automotive type carburetor to supply it with a fuel and air mixture and a standard spark plug to ignite the combustible mixture. Alternatively it may be fuel injected and achieve diesel ignition if a combustion operated valve is used. The design is simple to manufacture and inexpensive, and more efficiently produces a competitive power to weight ratio compared to automotive type internal combustion engines.  
       SUMMARY OF THE INVENTION  
       [0003]     The invention is a gas turbine engine comprised of a housing assembly divided horizontally along the axis of compressor shaft holes. Bolt holes passing through the top half of the housing assembly thread into the bottom half of the housing assembly bolting the two housing halves securely together. End plates bolt to each end of the housing assembly and have bearing enclosures projecting from their outer walls. Two compressor shaft holes pass through the housing assembly from one end to the opposite end and enclose two compressor shafts. Each compressor shaft carries on it a center compressor rotor and to each side of this compressor rotor is a turbine or paddlewheel rotor. The housing assembly contains appropriate enclosures to enclose the compressor shafts, the compressor rotors and the paddlewheel or turbine rotors.  
         [0004]     A center compressor compresses air and fuel into a compressor discharge passage. An intake port formed in the top of the housing assembly passes air to the compressor. In one embodiment a carburetor is fastened to the housing assembly top wall above this intake port. Spark ignition devices thread into the bottom housing wall into the ignition holes and ignite the fuel mixture. In one embodiment the compressor discharge passage extends from an ignition hole located in an inside housing wall to another ignition hole located in another inside housing wall. Combustion passages connect these ignition holes to the outer walls of turbine rotor holes in between the turbines on their downstream side. The burning gases are pumped by a gear pump compressor up through the ignition holes into the combustion passages and in between each set of turbines. The high pressure gas flows through the turbines forcing them to accelerate in opposite directions driving the counter rotating compressor rotors. The exhaust gases pass out of exhaust ports formed in the sides of the housing assembly.  
         [0005]     In another embodiment the ignition holes located in the housing walls between the compressor rotor holes and the turbine rotor holes connect to the center compressor discharge passage and combustion passages that project outward to the outer walls of the turbine rotor holes in between the turbines on their upstream side. Spark ignition devices thread into the ignition holes and ignite the fuel and air mixture in them. Combustion gas is pumped into the two sets of turbine holes and forces its way in between the turbine rotors forcing them to accelerate, driving the compressor, and passes out of the engine through top exhaust ports.  
         [0006]     In all embodiments specified and illustrated, an engine management system well known in the art, including sensor means, transducer means, connection means, control means, computer means, and accessory means such as fuel supply means, current supply means, coolant supply means, and starting and stopping means and any performance enhancing means available may be used to completely control engine performance characteristics to achieve maximum power, efficiency, and reliability.  
     
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
     Submitted with Preliminary Drawings  
       [0007]     1.  FIG. 1  is a top view of a wire frame illustration of a gas turbine engine in accordance with one embodiment of the invention.  
         [0008]     2.  FIG. 2  is a front view of a wire frame illustration of the gas turbine engine shown in  FIG. 1 .  
         [0009]     3.  FIG. 3  is a side view of a wire frame illustration of the gas turbine engine shown in  FIG. 1   
         [0010]     4.  FIG. 4  is a top view of a wire frame illustration of the housing of the gas turbine engine shown in  FIG. 1 .  
         [0011]     5.  FIG. 5  is a front view of a wire frame illustration of the housing of the gas turbine engine shown in  FIG. 1 .  
         [0012]     6.  FIG. 6  is a side view of a wire frame illustration of the housing of the gas turbine engine shown in  FIG. 1 .  
         [0013]     7.  FIG. 7  is a top view of a wire frame illustration of a gas turbine engine in accordance with another embodiment of the invention.  
         [0014]     8.  FIG. 8  is front view of a wire frame illustration of the gas turbine engine shown in  FIG. 7 .  
         [0015]     9.  FIG. 9  is a side view of a wire frame illustration of the gas turbine engine shown in  FIG. 7 .  
         [0016]     10.  FIG. 10  is a front view of a wire frame illustration of an alternative compressor shaft of the gas turbine engine shown in  FIG. 7 .  
         [0017]     11.  FIG. 11  is a front view of a wire frame illustration of the gas turbine engine using the compressor shaft shown in  FIG. 10 .  
         [0018]     12.  FIG. 12  is a diagram of an engine management system and the parts connected to it, well known in the art, used to control engine functioning. 
     
    
     DESCRIPTION OF THE PREFERRED EMBODIMENTS  
       [0019]     Referring now to the drawings in detail,  FIG. 1 - FIG. 6 ,  FIG. 12  illustrate a gas turbine engine constructed in accordance with one embodiment generally referred to by reference number  10 . In this embodiment the engine is enclosed by a housing assembly  20  containing a compressor rotor  21  having a drive shaft  22 , extending from one side, which has a turbine rotor  23  that is round and extends from the surface of the drive shaft  22 , a drive shaft  24  extending from the other side which has a turbine rotor  25  that is round and extends from the surface of the drive shaft  24 . The drive shafts  22  and  24  are a smaller diameter between the compressor rotor  21  and the turbine rotors  23  and  25 . The housing assembly  20  also contains a compressor rotor  26  having a drive shaft  27  extending from one side which has a turbine rotor  28  that is round and extends from the surface of the drive shaft  27 , and a drive shaft  29  extending from the other side which has a turbine rotor  30  that is round and extends from the surface of the drive shaft  29 . The drive shafts  27  and  29  are a smaller diameter between the compressor rotor  26  and the turbine rotors  28  and  30 . The compressor rotors  21  and  26  form part of the compressor of the engine. The turbine rotors  23 ,  25 ,  28 , and  30  form part of the turbine of the engine.  
         [0020]     The housing space contains the drive shaft  22  which extends through a compressor drive shaft hole  31  in an outer housing wall  32  and is supported by a bearing  33  enclosed in a bearing enclosure  34  projecting from an outside surface of the outer housing wall  32 . The drive shaft  24  extends through the compressor drive shaft hole  31  in an opposite outer housing wall  35  and is supported by a bearing  36  enclosed in a bearing enclosure  37  projecting from an outside surface of the opposite outer housing wall  35 . The drive shaft  27  extends through a compressor drive shaft hole  38  in the outer housing wall  32  and is supported by a bearing  39  enclosed in a bearing enclosure  40  projecting from an outside surface of the outer housing wall  32 . The drive shaft  29  extends through the compressor drive shaft hole  38  in the opposite outer housing wall  35  and is supported by a bearing  41  enclosed in a bearing enclosure  42  projecting from an outside surface of the opposite outer housing wall  35 .  
         [0021]     The housing assembly  20  has formed within it a compressor rotor hole  43 , with a turbine rotor hole  44  formed to one side and a turbine rotor hole  45  formed to the opposite side. The compressor drive shaft hole  31  passes from the outside of the bearing enclosure  34  to the outside of the bearing enclosure  37  and is axially aligned with the compressor rotor hole  43  and the turbine rotor holes  44  and  45 . The drive shaft hole  31  is a smaller diameter between the compressor rotor hole  43  and the turbine rotor holes  44  and  45 . The housing assembly  20  has formed within it a compressor rotor hole  46 , with a turbine rotor hole  47  formed to one side and a turbine rotor hole  48  formed to the opposite side. The compressor drive shaft hole  38  passes from the outside of the bearing enclosure  40  to the outside of the bearing enclosure  42  and is axially aligned with the compressor rotor hole  46  and the turbine rotor holes  47  and  48 . The drive shaft hole  38  is a smaller diameter between the compressor rotor hole  46  and the turbine rotor holes  47  and  48 .  
         [0022]     The turbine rotor  23  axially aligns within the turbine rotor hole  44 , the compressor rotor  21  axially aligns within the compressor rotor hole  43 , the turbine rotor  25  axially aligns within the turbine rotor hole  45 , the drive shaft  22  and the drive shaft  24  axially align within the compressor drive shaft hole  31 . The turbine rotor  28  axially aligns within the turbine rotor hole  47 , the compressor rotor  26  axially aligns within the compressor rotor hole  46 , the turbine rotor  30  axially aligns within the turbine rotor hole  48 , the drive shaft  27  and the drive shaft  29  axially align within the compressor output shaft hole  38 . The compressor rotors  21  and  26  mesh together inside the compressor rotor holes  43  and  46  to form a positive displacement gear pump that functions as the engine compressor.  
         [0023]     An exhaust port  49  projects through the side of the housing assembly  20  into the turbine rotor hole  44 , an exhaust port  50  projects through the side of the housing assembly  20  into the turbine rotor hole  47 , an exhaust port  51  projects through the side of the housing assembly  20  into the turbine rotor hole  45 , an exhaust port  52  projects through the side of housing assembly  20  into the turbine rotor hole  48 . The housing assembly  20  is divided in half along the axis of the compressor drive shaft hole  31  and the compressor drive shaft hole  38  and bolts passing through the top housing half thread into the bottom housing half to secure the housing halves together.  
         [0024]     An intake port  53  is formed in the top of the housing assembly  20 , and a carburetor  54  or a fuel injector is attached to the top of the housing assembly  20  and form part of the fuel supply of the engine. The carburetor  54  or the fuel injector, if used, are axially aligned with the intake port  53 . A throttle butterfly valve  56  is located in the carburetor barrel to control air flow. An ignition hole  57  projects through the housing bottom wall  58  up through the center of the inner housing wall  59  located between the compressor rotor holes  43  and  46  and the turbine rotor holes  44  and  47 . A bolt hole  60  located to one side of the ignition hole  57  and a bolt hole  61  located to the other side of the ignition hole  57  project up through the inner housing wall  59  passing from the bottom to the top of the housing assembly  20 . A spark ignition device  62  threads into the ignition hole  57 , so the electrode is located inside the ignition hole  57 , and fastens against the housing bottom wall  58 , to form part of the ignition system of the engine. An ignition hole  63  projects through the housing bottom wall  58  up through the center of the inner housing wall  64  located between the compressor rotor holes  43  and  46  and the turbine rotor holes  45  and  48 . A bolt hole  65  located to one side of the ignition hole  63  and a bolt hole  66  located to the other side of the ignition hole  63  project up through the inner housing wall  64  passing from the bottom to the top of the housing assembly  20 . A spark ignition device  67  threads into the ignition hole  63 , so the electrode is located inside the ignition hole  63 , and fastens against the housing bottom wall  58 . Bolts thread into the bottom half of the bolt holes  60 ,  61 ,  65 , and  66  and fasten the carburetor  54  to the housing assembly  20 .  
         [0025]     A combustion passage  68  is formed in the housing assembly  20  between the outer walls of the turbine rotor holes  44  and  47  and passes horizontally through the housing assembly  20  connecting to the ignition hole  57 . A combustion passage  69  is formed in the housing assembly  20  between the outer walls of the turbine rotor holes  45  and  48  and passes horizontally through the housing assembly  20  connecting to the ignition hole  63 . A compressor discharge passage  70  connects the ignition hole  57  to the ignition hole  63 .  
         [0026]     A top horizontal coolant passage  71  formed in the housing top wall  72  extends from inside one side of the housing assembly  20  to inside the opposite side and from behind the housing front wall  32  to in front of the housing back wall  35 . A vertical coolant passage  75  is formed in the inner housing wall  59  and is located between the compressor rotor hole  43  and the turbine rotor hole  44  and connects to the top horizontal cooling passage  71  and extends downward surrounding the drive shaft  22 . A vertical coolant passage  76  is formed in the inner housing wall  59  and is located between the compressor rotor hole  46  and the turbine rotor hole  47  and connects to the top horizontal cooling passage  71  and extends downward surrounding the drive shaft  27 . A vertical coolant passage  77  is formed in the inner housing wall  64  and is located between the compressor rotor hole  43  and the turbine rotor hole  45  and connects to the top horizontal cooling passage  71  and extends downward surrounding the drive shaft  24 . A vertical coolant passage  78  is formed in the inner housing wall  64  and is located between the compressor rotor hole  46  and the turbine rotor hole  48  and connects to the top horizontal cooling passage  71  and extends downward surrounding the drive shaft  29 .  
         [0027]     A side horizontal coolant passage  79  connects the vertical coolant passage  75  and the vertical coolant passage  77  together and extends from behind the housing front wall  32  to in front of the housing back wall  35 . A side horizontal coolant passage  80  connects the vertical coolant passage  76  and the vertical coolant passage  78  together and extends from behind the housing front wall  32  to in front of the housing back wall  35 .  
         [0028]     A coolant inlet hole  81  passes through the housing top wall  72  and connects to the top horizontal coolant passage  71 . A coolant inlet flange  82  projects upward from the surface of the housing top wall  72  and is axially aligned with the coolant inlet hole  81 . A coolant outlet hole  83  passes through the housing bottom wall  58  connecting to the side horizontal coolant passage  80 . A coolant outlet flange  84  projects downward from the surface of the housing bottom wall  58  and is axially aligned with the coolant outlet hole  83 .  
         [0029]     To start the engine an on/off switch is thrown to energize a starter  87  that rotates the drive shaft  24 . Rotation of the drive shaft  24  rotates the compressor rotor  21 . Rotation of the compressor rotor  21  rotates the compressor rotor  26  and the compressor draws air into the engine through the intake port  53 , through the carburetor  54 , and the fuel/air mixture is discharged into the compressor discharge passage  70  and flows into the ignition holes  57  and  63 . The spark ignition devices  62  and  67  ignite the fuel mixture and the hot gases pass into the combustion passages  68  and  69 . Gases in the combustion passage  68  flows into the turbine rotor holes  44  and  47  and the gas pressure between the counter rotating turbine rotors  23  and  28  drives them in opposite directions accelerating them. Gases in the combustion passage  69  flows into the turbine rotor holes  45  and  48  and the gas pressure between the counter rotating turbine rotors  25  and  30  drives them in opposite directions accelerating them. The turbine rotors  23  and  25  drive the drive shafts  22  and  24  which drive the compressor rotor  21 . The turbine rotors  28  and  30  drive the drive shafts  27  and  29  which drive the compressor rotor  26 . Gas pressure driving the turbine rotors  23 ,  25 ,  28 , and  30  passes out of the side exhaust ports  49 ,  50 ,  51 , and  52 . Acceleration of the compressor rotors  21  and  26  draws more air through the carburetor  54  increasing the amount of fuel and air burned per unit time increasing the engines power. A coolant pump  85  pumps coolant through the engine coolant passages, a fuel pump  86  supplies fuel, and an alternator  88  supplies running current. An engine management system controls engine operation and performance.  
         [0030]     Referring now to the drawings in detail,  FIG. 7 - FIG. 12  illustrate a gas turbine engine constructed in accordance with a second embodiment generally referred to by reference number  10 ′. In this embodiment the engine is enclosed by a housing assembly  20 A containing a compressor rotor  21 ′, having a drive shaft  22 A, extending from one side which has a turbine rotor  23 A, that is round and extends from the surface of the drive shaft  22 A, and a drive shaft  24 A, extending from the other side which has a turbine rotor  25 A, that is round and extends from the surface of the drive shaft  24 A. The housing  20 A also contains a compressor rotor  26 ′, having a drive shaft  27 A, extending from one side which has a turbine rotor  28 A, that is round and extends from the surface of the drive shaft  27 A, and a drive shaft  29 A extending from the other side which has a turbine rotor  30 A, that is round and extends from the surface of the drive shaft  29 A. The compressor rotors  21 ′ and  26 ′ form part of the compressor of the engine. The turbine rotors  23 A,  25 A,  28 A, and  30 A form part of the turbine of the engine.  
         [0031]     The drive shaft  22 A extends through a compressor drive shaft hole  31 A, in a detachable outer housing wall  32 A and is supported by a bearing  33 ′ enclosed in a bearing enclosure  34 ′ projecting from an outside surface of the detachable outer housing wall  32 A. The drive shaft  24 A extends through the compressor drive shaft hole  31 A in an opposite detachable outer housing wall  35 A and is supported by a bearing  36 ′ enclosed in a bearing enclosure  37 ′ projecting from an outside surface of the opposite detachable outer housing wall  35 A. The drive shaft  27 A extends through a compressor drive shaft hole  38 A in the detachable outer housing wall  32 A and is supported by a bearing  39 ′ enclosed in a bearing enclosure  40 ′ projecting from an outside surface of the detachable outer housing wall  32 A. The drive shaft  29 A extends through the compressor output shaft hole  38 A in the opposite detachable outer housing wall  35 A and is supported by a bearing  41 ′ enclosed in a bearing enclosure  42 ′ projecting from an outside surface of the opposite detachable outer housing wall  35 A.  
         [0032]     The housing assembly  20 A has formed within it a compressor rotor hole  43 ′, with a turbine rotor hole  44 A, formed to one side and a turbine rotor hole  45 A, formed to the opposite side. The compressor drive shaft hole  31 A passes from the outside of the bearing enclosure  34 ′ to the outside of the bearing enclosure  37 ′ and is axially aligned with the compressor rotor hole  43 ′ and the turbine rotor holes  44 A and  45 A. The housing assembly  20 A has formed within it a compressor rotor hole  46 ′, with a turbine rotor hole  47 A, formed to one side and a turbine rotor hole  48 A, formed to the opposite side. The compressor drive shaft hole  38 A passes from the outside of the bearing enclosure  40 ′ to the outside of the bearing enclosure  42 ′ and is axially aligned with the compressor rotor hole  46 ′ and the turbine rotor holes  47 A and  48 A.  
         [0033]     The turbine rotor  23 A axially aligns within the turbine rotor hole  44 A, the compressor rotor  21 ′ axially aligns within the compressor rotor hole  43 ′, the turbine rotor  25 A axially aligns within the turbine rotor hole  45 A, the drive shaft  22 A and the drive shaft  24 A axially align within the compressor drive shaft hole  31 A. The turbine rotor  28 A axially aligns within turbine rotor hole  47 A, the compressor rotor  26 ′ axially aligns within the compressor rotor hole  46 ′, the turbine rotor  30 A axially align within the turbine rotor hole  48 A, the drive shaft  27 A and the drive shaft  29 A axially align within the compressor drive shaft hole  38 A. The compressor rotors  21 ′ and  26 ′ mesh together inside compressor rotor holes  43 ′ and  46 ′ to form a positive displacement gear pump that functions as the engine compressor. A lobular gear type compressor shown in  FIG. 10  and  FIG. 11  may be used.  
         [0034]     An exhaust port  49 A projects down through the housing assembly  20 A into the turbine rotor holes  44 A and  47 A. An exhaust port  50 A projects down through the housing assembly  20 A into the turbine rotor hole  45 A and  48 A. The housing assembly  20 A is divided in half along the axis of the compressor drive shaft hole  31 A and the compressor drive shaft hole  38 A and bolts passing through the top housing half thread into the bottom housing half to secure the housing halves together.  
         [0035]     An intake port  53 ′ is formed in the top of the housing assembly  20 A. An injector holder  54 A is formed within the intake port  53 ′ and a fuel injector  55  is secured inside the injector holder  54 A. The fuel injector  55  is axially aligned with the intake port  53 ′. All turbine rotors have side walls  56 A. An ignition hole  57 A projects through the housing bottom wall  58 A up through the center of the inner housing wall  59 ′ located between the compressor rotor holes  43 ′ and  46 ′ and the turbine rotor holes  44 A and  47 A. A bolt hole  60 ′ located to one side of the ignition hole  57 A and a bolt hole  61 ′ located to the other side of the ignition hole  57 A project up through the inner housing wall  59 ′ passing from the bottom to the top of the housing assembly  20 A. A spark ignition device  62 ′ threads into the ignition hole  57 A, so the electrode is located inside the ignition hole  57 ′, and fastens against the housing bottom wall  58 ′. An ignition hole  63 A projects through the housing bottom wall  58 ′ up through the center of the inner housing wall  64 ′ located between the compressor rotor holes  43 ′ and  46 ′ and the turbine rotor holes  45 A and  48 A. A bolt hole  65 ′ located to one side of the ignition hole  63 A and a bolt hole  66 ′ located to the other side of the ignition hole  63 A project up through the inner housing wall  64 ′ passing from the bottom to the top of the housing assembly  20 A. A spark ignition device  67 ′ threads into the ignition hole  63 A, so the electrode is located inside the ignition hole  63 A, and fastens against the housing bottom wall  58 ′. Bolts thread into the bolt holes  60 ′,  61 ′,  65 ′, and  66 ′ in the housing assembly bottom half and fasten the halves of the housing assembly  20 A together.  
         [0036]     A combustion passage  68 A is formed in the housing assembly  20 A from the outer walls of the turbine rotor holes  44 A and  47 A and passes horizontally through the housing assembly  20 A connecting to the ignition hole  57 A. A combustion passage  69 A is formed in the housing assembly  20 A from the outer walls of the turbine rotor holes  45 A and  48 A and passes horizontally through the housing assembly  20 A connecting to the ignition hole  63 A. A compressor discharge passage  70 ′ connects the ignition hole  57 A to the ignition hole  63 A.  
         [0037]     A vertical coolant passage  75 ′ is formed in the inner housing wall  59 ′ and is located between the compressor rotor hole  43 ′ and the turbine rotor hole  44 A and extends downward partially surrounding the drive shaft  22 A. A vertical coolant passage  76 ′ is formed in the inner housing wall  59 ′ and is located between the compressor rotor hole  46 ′ and the turbine rotor hole  47 A and extends downward partially surrounding the drive shaft  27 A. A vertical coolant passage  77  is formed in the inner housing wall  64 ′ and is located between the compressor rotor hole  43 ′ and the turbine rotor hole  45 A and extends downward partially surrounding the drive shaft  24 A. A vertical coolant passage  78 ′ is formed in the inner housing wall  64 ′ and is located between the compressor rotor hole  46 ′ and the turbine rotor hole  48 A and extends downward partially surrounding the drive shaft  29 A.  
         [0038]     A semi-circle horizontal coolant passage  79 A connects the vertical coolant passage  75 ′ and the vertical coolant passage  77 ′ together and extends from the detachable housing front wall  32 A to the detachable housing back wall  35 A. A semi-circle horizontal coolant passage  80 A connects the vertical coolant passage  76 ′ and the vertical coolant passage  78 ′ together and extends from the detachable housing front wall  32 A to the detachable housing back wall  35 A.  
         [0039]     A coolant inlet hole  81 ′ passes through the housing top wall  72 ′ and connects to the semi-circle horizontal coolant passage  80 A. A coolant inlet flange  82 ′ projects upward from the surface of the housing top wall  72 ′ and is axially aligned with the coolant inlet hole  81 ′. A coolant outlet hole  83 ′ passes through the housing bottom wall  58 ′ and connects to the semi-circle horizontal coolant passage  79 A. A coolant outlet flange  84 ′ projects downward from the surface of the housing bottom wall  58 ′ and is axially aligned with the coolant outlet hole  83 ′.  
         [0040]     To start the engine an on/off switch is thrown to energize a starter  87 ′ that rotates the drive shaft  24 A. Rotation of the drive shaft  24 A rotates the compressor rotor  21 ′. Rotation of compressor rotor  21 ′ rotates the compressor rotor  26 ′ and the compressor draws air into the engine through the intake port  53 ′. The fuel injector  55  injects fuel into the intake port  53 ′ and the fuel/air mixture is discharged into the compressor discharge passage  70 ′ and flows into the ignition holes  57 A and  63 A. The spark ignition devices  62 ′ and  67 ′ ignite the fuel mixture and the hot gases pass into the combustion passages  68 A and  69 A. Gases in the combustion passage  68 A flow into the turbine rotor holes  44 A and  47 A and the gas pressure between the counter rotating turbine rotors  23 A and  28 A drives them in opposite directions accelerating them. Gas driving the turbine rotors  23 A and  28 A passes out of the top exhaust port  49 A. Gases in the combustion passage  69 A flow into turbine rotor holes  45 A and  48 A and the gas pressure between the counter rotating turbine rotors  25 A and  30 A drives them in opposite directions accelerating them. Gas driving the turbine rotors  25 A and  30 A passes out of the top exhaust port  50 A. The turbine rotors  23 A and  25 A drive the drive shafts  22 A and  24 A which drive the compressor rotor  21 ′. The turbine rotors  28 A and  30 A drive the drive shafts  27 A and  29 A which drive the compressor rotor  26 ′. Acceleration of the compressor rotors  21 ′ and  26 ′ draws in more air and the fuel injector  55  injects more fuel into the engine increasing the amount of fuel and air burned per unit time increasing the engines power. A coolant pump  85 ′ pumps coolant through the engine coolant passages, a fuel pump  86 ′ supplies fuel, and an alternator  88 ′ supplies running current. An engine management system controls engine operation and performance.  
         [0041]      FIG. 10  and  FIG. 11  show a version of the second embodiment using a lobular gear compressor. Compressor rotors  21 A and  26 A replace compressor rotors  21 ′ and  26 ,′ turbines  23 B,  25 B,  28 B, and  30 B replace turbines  23 A,  25 A,  28 A, and  30 A, turbine holes  44 B,  45 B,  47 B, and  48 B replace turbine holes  44 A,  45 A,  47 A, and  48 A, drive shafts  22 B,  24 B,  27 B, and  29 B replace drive shafts  22 A,  24 A,  27 A, and  29 A, drive shaft holes  31 B and  38 B replace drive shaft holes  31 A and  38 A, bolt holes  60 A,  61 A,  65 A, and  66 A replace bolt holes  60 ′,  61 ′,  65 ′, and  66 ′, and semi-circle horizontal coolant passages  79 B and  80 B replace semi-circle horizontal coolant passages  79 A and  80 A. The engine functions the same way and the other parts of the machine are the same.  
         [0042]     While the preferred embodiments of the invention have been shown and described, it is to be understood that the disclosure is for the purpose of illustration and that various changes and modifications may be made without departing from the scope of the invention as set forth in the appended claims.  
       PARTS  
       [0000]    
       
           10 —GAS TURBINE ENGINE  
           20 —HOUSING ASSEMBLY  
           21 —COMPRESSOR ROTOR 1   
           22 —DRIVE SHAFT 1   
           23 —TURBINE ROTOR 1   
           24 —DRIVE SHAFT 2   
           25 —TURBINE ROTOR 2   
           26 —COMPRESSOR ROTOR 2   
           27 —DRIVE SHAFT 3   
           28 —TURBINE ROTOR 3   
           29 —DRIVE SHAFT 4   
           30 —TURBINE ROTOR 4   
           31 —COMPRESSOR DRIVE SHAFT HOLE 1   
           32 —OUTER HOUSING WALL 1   
           33 —BEARING 1   
           34 —BEARING ENCLOSURE 1   
           35 —OPPOSITE OUTER HOUSING WALL 2   
           36 —BEARING 2   
           37 —BEARING ENCLOSURE 2   
           38 —COMPRESSOR DRIVE SHAFT HOLE 2   
           39 —BEARING 3   
           40 —BEARING ENCLOSURE 3   
           41 —BEARING 4   
           42 —BEARING ENCLOSURE 4   
           43 —COMPRESSOR ROTOR HOLE 1   
           44 —TURBINE ROTOR HOLE 1   
           45 —TURBINE ROTOR HOLE 2   
           46 —COMPRESSOR ROTOR HOLE 2   
           47 —TURBINE ROTOR HOLE 3   
           48 —TURBINE ROTOR HOLE 4   
           49 —EXHAUST PORT 1   
           50 —EXHAUST PORT 2   
           51 —EXHAUST PORT 3   
           52 —EXHAUST PORT 4   
           53 —INTAKE PORT  
           54 —CARBURETOR  
           56 —THROTTLE BUTTERFLY VALVE  
           57 —IGNITION HOLE 1   
           58 —HOUSING BOTTOM WALL  
           59 —INNER HOUSING WALL 1   
           60 —BOLT HOLE 1   
           61 —BOLT HOLE 2   
           62 —SPARK IGNITION DEVICE 1   
           63 —IGNITION HOLE 2   
           64 —INNER HOUSING WALL 2   
           65 —BOLT HOLE 3   
           66 —BOLT HOLE 4   
           67 —SPARK IGNITION DEVICE 2   
           68 —COMBUSTION PASSAGE 1   
           69 —COMBUSTION PASSAGE 2   
           70 —COMPRESSOR DISCHARGE PASSAGE  
           71 —TOP HORIZONTAL COOLANT PASSAGE  
           72 —HOUSING TOP WALL  
           75 —VERTICAL COOLANT PASSAGE 1   
           76 —VERTICAL COOLANT PASSAGE 2   
           77 —VERTICAL COOLANT PASSAGE 3   
           78 —VERTICAL COOLANT PASSAGE 4   
           79 —SIDE HORIZONTAL COOLANT PASSAGE 1   
           80 —SIDE HORIZONTAL COOLANT PASSAGE 2   
           81 —COOLANT INLET HOLE  
           82 —COOLANT INLET FLANGE  
           83 —COOLANT OUTLET HOLE  
           84 —COOLANT OUTLET FLANGE  
           85 —COOLANT PUMP  
           86 —FUEL PUMP  
           87 —STARTER  
           88 —ALTERNATOR  
           10 ′—GAS TURBINE ENGINE  
           20 A—HOUSING ASSEMBLY  
           21 ′—COMPRESSOR ROTOR 1   
           21 A—COMPRESSOR ROTOR 1   
           22 A—DRIVE SHAFT 1   
           22 B—DRIVE SHAFT 1   
           23 A—TURBINE ROTOR 1   
           23 B—TURBINE ROTOR 1   
           24 A—DRIVE SHAFT 2   
           24 B—DRIVE SHAFT 2   
           25 A—TURBINE ROTOR 2   
           25 B—TURBINE ROTOR 2   
           26 ′—COMPRESSOR ROTOR 2   
           26 A—COMPRESSOR ROTOR 2   
           27 A—DRIVE SHAFT 3   
           27 B—DRIVE SHAFT 3   
           28 A—TURBINE ROTOR 3   
           28 B—TURBINE ROTOR 3   
           29 A—DRIVE SHAFT 4   
           29 B—DRIVE SHAFT 4   
           30 A—TURBINE ROTOR 4   
           30 B—TURBINE ROTOR 4   
           31 A—COMPRESSOR DRIVE SHAFT HOLE 1   
           31 B—COMPRESSOR DRIVE SHAFT HOLE 2   
           32 A—DETACHABLE OUTER HOUSING WALL 1   
           33 ′—BEARING 1   
           34 ′—BEARING ENCLOSURE 1   
           35 A—OPPOSITE DETACHABLE OUTER HOUSING WALL 2   
           36 ′—BEARING 2   
           37 ′—BEARING ENCLOSURE 2   
           38 A—COMPRESSOR DRIVE SHAFT HOLE 2   
           38 B—COMPRESSOR DRIVE SHAFT HOLE  
           39 ′—BEARING 3   
           40 ′—BEARING ENCLOSURE 3   
           41 ′—BEARING 4   
           42 ′—BEARING ENCLOSURE 4   
           43 ′—COMPRESSOR ROTOR HOLE 1   
           44 A—TURBINE ROTOR HOLE 1   
           44 B—TURBINE ROTOR HOLE 1   
           45 A—TURBINE ROTOR HOLE 2   
           45 B—TURBINE ROTOR HOLE 2   
           46 ′—COMPRESSOR ROTOR HOLE 2   
           47 A—TURBINE ROTOR HOLE 3   
           47 B—TURBINE ROTOR HOLE 3   
           48 A—TURBINE ROTOR HOLE 4   
           48 B—TURBINE ROTOR HOLE 4   
           49 A—EXHAUST PORT 1   
           50 A—EXHAUST PORT 2   
           53 ′—INTAKE PORT  
           54 A—INJECTOR HOLDER  
           55 —FUEL INJECTOR  
           56 A—TURBINE SIDE WALL  
           57 A—IGNITION HOLE 1   
           58 ′—HOUSING BOTTOM WALL  
           59 ′—INNER HOUSING WALL 1   
           60 ′—BOLT HOLE 1   
           60 A—BOLT HOLE 1   
           61 ′—BOLT HOLE 2   
         
           62 
           a—BOLT HOLE 2   
         
           62 ′—SPARK IGNITION DEVICE 1   
           63 A—IGNITION HOLE 2   
           64 ′—INNER HOUSING WALL 2   
           65 ′—BOLT HOLE 3   
           65 A—BOLT HOLE 3   
           66 ′—BOLT HOLE 4   
           66 A —BOLT HOLE 4   
           67 ′—SPARK IGNITION DEVICE 2   
           68 A—COMBUSTION PASSAGE 1   
           69 A—COMBUSTION PASSAGE 2   
           70 ′—COMPRESSOR DISCHARGE PASSAGE  
           72 ′—HOUSING TOP WALL  
           75 ′—VERTICAL COOLANT PASSAGE 1   
           76 ′—VERTICAL COOLANT PASSAGE 2   
           77 ′—VERTICAL COOLANT PASSAGE 3   
           78 ′—VERTICAL COOLANT PASSAGE 4   
           79 A—SEMI-CIRCLE HORIZONTAL COOLANT PASSAGE 1   
           79 B—SEMI-CIRCLE HORIZONTAL COOLANT PASSAGE 1   
           80 A—SEMI-CIRCLE HORIZONTAL COOLANT PASSAGE 2   
           80 B—SEMI-CIRCLE HORIZONTAL COOLANT PASSAGE 2   
           81 ′—COOLANT INLET HOLE  
           82 ′—COOLANT INLET FLANGE  
           83 ′—COOLANT OUTLET HOLE  
           84 ′—COOLANT OUTLET FLANGE  
           85 ′—COOLANT PUMP  
           86 ′—FUEL PUMP  
           87 ′—STARTER  
           88 ′—ALTERNATOR