Abstract:
The invention is a turbojet propulsion system which includes a compressor section, a turbine section coupled by a shaft to the compressor section, a combustion section mounted between the compressor section and the turbine section, and an exhaust duct coupled to the aft end of said turbine section. A fuel delivery system is incorporated for supplying fuel to the combustion section. A laser assembly provides electromagnetic radiation to the combustion section. An electrical generator coupled to the turbine driven shaft powers the laser assembly.

Description:
BACKGROUND OF THE INVENTION  
       [0001]     1. Field of the Invention  
         [0002]     The invention relates to the field of propulsion systems and, in particular, to a turbojet propulsion system wherein lasers are used to add additional energy to the combustion process.  
         [0003]     2. Description of Related Art  
         [0004]     Recent Defense Advanced Research Projects Agency (DARPA) advances in the field of Diode Pumped Solid State Laser Technology, specifically Fiber Lasers, have enabled scalable and robust system packaging architectures for operation in harsh environments. These next generation fiber laser systems require minimal thermal management and possess a relatively small footprint within an integrated assembly. The combination of a laser diode pump and an optical fiber gain medium makes possible extremely compact packages suitable for a diversity of applications. State of the art solid-state laser technology comprises three principal components, namely the lasing material (active medium), the optical pump source, and the optical cavity (resonator). The lasing material can be Ytterbium-Yttrium Aluminum Garnet (Yb-YAIG) crystal, or Yfterbium/Erbium-Ytterbium doped optical fiber. The optical pump source (flash lamp, laser diode or fiber laser) adds energy to the lasing material to cause electron collisions, and hence radiation from a laser, by principle of population inversion.  
         [0005]     Transmitting laser energy from some platform (ground, airborne, or orbiting) through an optical window to heat a working fluid, has been investigated either theoretically or experimentally by NASA among other organizations. Examples of these types of propulsion systems can be found in U.S. Pat. No. 4,036,012, Laser Powered Rocket Engine Using A Gas Dynamic Window by M. L, Monsler; U.S. Pat. No. 6,459,205, Propulsion System And Method Of Generating Shockwaves by W. Schall, et al.; U.S. Pat. No. 6,488,233, Laser Propelled Vehicle by L. N Myrabo and U.S. Pat. No. 5,152,135, Reflector For Efficient Coupling Of A Laser Beam To Air Or Other Fluids by J. T. K. Because they all utilize external (not on-board) laser systems to generate gas dynamic propulsion, they have limited use and application.  
         [0006]     U.S. Pat. No. 6,385,963, Optical System For Generating Endothermic Fuel For Use In A Propulsion System By J. H. Hunt, et al discloses a rocket engine wherein fuel and oxidizer are injected into a thrust chamber and ignited. A laser system is used to heat the fuel to a temperature wherein it dissociates prior to injection into the combustion chamber, thus increasing the energy available to produce thrust. U.S. Pat. No. 5,542,247, Apparatus Powered Using Laser Supplied Energy by B. B. Bushman discloses both rocket engine and turbojet engine concepts wherein the laser is used within the combustion chamber for disassociation of the air molecules, producing pressure waves, consequently providing thrust. However, this latter concept does not address the power required to actuate the laser.  
         [0007]     Thus, it is a primary object of the invention to provide a propulsion system wherein lasers are used to provide increased thermal activity in the combustion chamber, thereby causing enhanced combustion and consequently augmenting thrust or power output.  
         [0008]     It is another primary object of the invention to provide a turbojet propulsion system wherein lasers are used to provide increased thermal activity in the combustion chamber.  
         [0009]     It is a further object of the invention to provide a propulsion system wherein lasers are used to provide increased thermal activity in the combustion chamber wherein the propulsion system provides the power for the laser.  
       SUMMARY OF THE INVENTION  
       [0010]     The invention is a turbojet propulsion system incorporating lasers to augment the combustion process. In detail, the propulsion system includes a compressor section, a turbine section coupled by a shaft to the compressor section, a combustion section mounted between the compressor section and the turbine section, and an exhaust duct (nozzle) coupled to the aft end of the turbine section. A fuel delivery system is included for supplying fuel to the combustion section. A laser assembly powered by an electrical generator driven of the shaft is used to provide intense electromagnetic radiation to the combustion section.  
         [0011]     The laser system includes a plurality of lasers coupled to the combustion section both circumferentially and along the longitudinal axis thereof. In one embodiment, the combustion section is in the shape of a hollow cylindrical ring having external and internal circumferential walls, the internal surfaces of the external and internal walls having laser beam reflecting surfaces. Preferably these internal surfaces are coated with high temperature resistant optical substrates such as Silicon Dioxide and Aluminum Oxide. The lasers of the laser assembly are positioned on the external wall to direct laser beams to the internal surface of the internal wall, such that the laser beams are reflected off the internal surface of the internal wall back toward the internal surface of the external wall. Preferably, the lasers are directed slightly off the longitudinal axis such that the laser beams reflected off the internal surface of the inner wall are not reflected directly back into the output optics of the laser which initiates the beam.  
         [0012]     In a second embodiment, the turbojet propulsion system includes a combustion section that includes a plurality of hollow cylinders formed into a ring, each having a centrally located longitudinal axis. The inner surface of the cylinders include a laser beam reflecting surface. The lasers are positioned on the external surfaces of each of the cylinders to direct laser beams into the cylinders such that the laser beams are reflected off the inner surface of the cylinder. Preferably the lasers are positioned on the external surface of the cylinders such that the laser beams do not pass through the longitudinal axis of the cylinders. The Fiber laser output ends can act as one way mirrors, in that light may pass through into the combustion cylinders, however reflected laser light may not be allowed back, so as to prevent damage to the laser beam output optics.  
         [0013]     The novel features which are believed to be characteristic of the invention, both as to its organization and method of operation, together with further objects and advantages thereof, will be better understood from the following description in connection with the accompanying drawings in which the presently preferred embodiments of the invention are illustrated by way of examples. It is to be expressly understood, however, that the drawings are for purposes of illustration and description only and are not intended as a definition of the limits of the invention.  
     
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0014]      FIG. 1  is a simplified schematic representation of a turbojet engine having a single annular shaped combustion chamber.  
         [0015]      FIG. 2  is an enlarged cross-sectional view of the turbojet engine shown in  FIG. 1  taken along the line  2 - 2 .  
         [0016]      FIG. 3  is a simplified schematic representation of a turbojet engine having a plurality of annular shaped combustion chambers mounted about the longitudinal axis thereof.  
         [0017]      FIG. 4  is an enlarged cross-sectional view of the turbojet engine shown in  FIG. 3  taken along the line  44 .  
         [0018]      FIG. 5  is a partial cross-sectional view of the combustion chamber shown in  FIG. 1  illustrating the attachment of the fiber optic laser thereto. 
     
    
     DESCRIPTION OF THE PREFERRED EMBODIMENT  
       [0019]     Referring to  FIG. 1 , the typical turbojet engine, generally indicated by numeral  10 , having a longitudinal axis  11 , The turbojet engine  10  includes a housing  12 , compressor section  14  combustion section  16 , turbine section  18  coupled by drive shaft  20  to the compressor, and an exhaust nozzle  22 . Fuel is provided to the combustion section  16  by means a fuel system that includes fuel lines  24  coupled to a fuel pump (not shown). Air enters the compressor section  14 , is compressed thereby; enters the combustion section where fuel is added and ignited the hot gases pass through the turbine section  18  wherein energy is extracted to power the compressor section and thereafter exits out the exhaust nozzle  22 . The combustion section  16  is ring shaped cylinder having an outer wall  30  and inner wall  32 , a closed off front end  34  with compressed air inlet ports  35  and fuel injectors  36  and a nozzle end  38  for directing hot gas to the turbine section  18 . While the above description is simplified, it is basic to all turbojet and turbo-shaft engines.  
         [0020]     As discussed in the prior art, a laser beam at the right frequency and power can disassociate air molecules as well as those of the fuel. Thus still referring to  FIG. 1  and additionally to  FIGS. 2 and 5 , laser assemblies  40 A and  40 B are positioned about the circumference of the outer wall  30  of the ring shaped combustion section  16  in rows along the longitudinal axis  11  and fiber optic cables  42 A and  42 B connect the laser arrays thereto. These fiber optic lasers can be obtained from Southampton Photonics, Southampton, in the United Kingdom, Spectra-Physics Corporation, Mountain View, Calif., or Aculight Corporation, Bothell, Wash. Referring to particularly to  FIG. 5 , each fiber optic cables  42 A and  42 B are coupled via holes  43  to the outer wall  30  of the combustion section  16 , such that the end  44  of the cable is almost flush with the inner surface  46  of the outer wall. The cable can be bonded using a high temperature resin or brazed in place. The end of the cable  46  is coated with a transparent protective layer of silicon oxide, indicated by numeral  48 . The inner surface  46  of the outer wall  30 , as well as the inner surface  50  of the inner wall  32  are coated with optical substrate  51  such as Silicon Dioxide and Aluminum Oxide. The number of arrays may vary with size and design requirements of the individual turbojet engine  10 .  
         [0021]     The Fiber laser has as combined resonator and active medium component its Ytterbium-doped fiber optic core, which is light-pumped by laser diodes connected directly to the turbine driven electrical generator, which powers them. The laser beam focusing optics is fused directly onto the fiber core output ends, thus minimizing space and assembly weight. Furthermore, multiple fiber cables can be coupled together and light-pumped in unison, in this manner increasing the fiber laser power output. These fiber lasers generate high energy photon beams which interact with both air and fuel molecules, consequently imparting their kinetic energy and thereby augmenting thermal activity within the combustion section.  
         [0022]     Preferably, the laser arrays  40 A and  40 B are powered by electric generator  60 . A gearbox  62  coupled to the shaft  20  between the compressor section  14  and combustion section  16  drives shaft  64  mounted on the housing  12 , which, in turn couples to gearbox  66  drivng the generator  60 .  
         [0023]     In a second version of the turbojet engine, generally designated by numeral  10 A, the combustion section, now indicated by numeral  16 A, includes a plurality of cylinders  70  spaced about the longitudinal axis  11 . Each cylinder  60  has a longitudinal axis  71  and includes a front end having air intake ports  72  and fuel inlet nozzle  74  coupled to fuel line  24 . The opposite end of cylinder terminates in an exhaust nozzle  66  that directs exhaust gases to the turbine section  18 . The laser arrays  80 A and  80 B couple to the cylinders  60  by means of fiber optic cables  82 A and  82 B. Again the laser impulses are directed slightly off the longitudinal axis  71  of the cylinders  70 .  
         [0024]     While the invention has been described with reference to a particular embodiment, it should be understood that the embodiments are merely illustrative as there are numerous variations and modifications, which may be made by those skilled in the art. Thus, the invention is to be construed as being limited only by the spirit and scope of the appended claims.  
       INDUSTRIAL APPLICABILITY  
       [0025]     The invention has applicability to aircraft propulsion industry.  
         [0026]     Referring to  FIG. 1 , the typical turbojet engine, generally indicated by numeral  10 , having a longitudinal axis  11 , The turbojet engine  10  includes a housing  12 , compressor section  14  combustion section  16 , turbine section  18  coupled by drive shaft  20  to the compressor, and an exhaust nozzle  22 . Fuel is provided to the combustion section  16  by means a fuel system that includes fuel lines  24  coupled to a fuel pump (not shown). Air enters the compressor section  14 , is compressed thereby; enters the combustion section where fuel is added and ignited and the hot gases pass through the turbine section  18  wherein energy is extracted to power the compressor section and thereafter exits out the exhaust nozzle  22 . The combustion section  16  is ring shaped cylinder having an outer wall  30  and inner wall  32 , a closed off front end  34  with compressed air inlet ports  35  and fuel injectors  36  and a nozzle end  38  for directing hot gas to the turbine section  18 . While the above description is simplified, it is basic to all turbojet and turbo-shaft engines.