Abstract:
A fuel processing system for a turbine engine includes a fuel processor which mixes fuel and air through a vortical flow which involves the introduction of air tangentially into the fuel processing chamber through inlet apertures formed in the outer wall of the fuel processing chamber. The vortical flow of fluid inside the fuel processing chamber breaks down or atomizes fuel such that the resulting fuel/air mixture will be ideal for combustion. The fuel/air mixture is thereafter introduced into a combustion chamber of the combustor of a turbine engine apparatus. One or more fuel processing units operatively coupled in series may be utilized.

Description:
FIELD OF THE INVENTION 
   This invention relates to turbine engines, and more particularly to fuel processing devices for use in connection with turbine engines. 
   BACKGROUND OF THE INVENTION 
   Turbine engines have existed for years. While turbine engines have traditionally been associated most closely with jet airplanes, turbine engines have also been used in connection with various other types of other areas with success. For example, turbine engines may be used for helicopters, turbo prop planes, land vehicles, ultralight planes, unlimited hydroplanes, military tanks, and hovercraft, as well as stationary and mobile power plants, just to name a few. 
   One of the key aspects to any turbine engine relates to the proper and efficient burning of fuel within the fuel combustion chamber of the turbine engine. As those skilled in the art understand, combustion of fuel in the combustion chamber creates heat which, in turn, drives a turbine fan and actuates the turbine engine. Increased fuel efficiency is always desirable in turbine engines. 
   Accordingly, there has been and continues to be a need to develop a more efficient way to process and burn fuel within a fuel combustion chamber of a gas turbine engine. The present invention solves the longstanding problems associated with improper or incomplete fuel processing and fuel combustion within a fuel combustion chamber of a turbine engine. 
   SUMMARY OF THE INVENTION 
   The present invention relates to a fuel processing apparatus for a turbine engine. The fuel processor of the present invention, takes incoming fuel, introduces fuel directly into a fuel mixing chamber, and introduces air tangentially into the fuel processing chamber through inlet apertures formed in an outer wall of the fuel processing chamber. The fuel processor configuration creates a vortical flow of fluid within the fuel processing chamber. The vortical flow of fluid inside the fuel processing chamber breaks down or atomizes the fuel such that the resulting fuel/air mixture will be ideal for combustion. The mixed fuel is introduced into a combustion chamber of the combustor of a turbine engine apparatus. 
   To create the vortical flow of fuel/air within the fuel mixing chamber, a plurality of apertures extend tangentially through an outer wall of the mixing chamber. The apertures cause air to be introduced tangentially into the fuel processing chamber which creates a vortical flow (i.e., a tornado-like flow) within the fuel processing chamber. The vortical flow causes the fuel/air mixture within the fuel processing chamber to impinge upon itself and further break down or atomize the fuel. 
   In one embodiment, a preliminary or initial fuel mixing chamber is coupled in series with a secondary or primary fuel processing chamber for optimal fuel processing. Alternatively, a single fuel processing chamber may be utilized. It will be understood by those skilled in the art that various fuel processing configurations may be utilized without departing from the scope of the present invention. 
   The foregoing and other features, utilities, and advantages of the invention will become apparent from the following more detailed description of the invention with reference to the accompanying drawings. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
       FIG. 1  is a diagrammatic view of a typical gas-turbine configuration exhibiting a Brayton or Joule cycle; 
       FIG. 2  is a sectional side elevation view of a fuel processing system according to the present invention; 
       FIG. 3  is a right side elevation view of the fuel processing system of  FIG. 2 ; 
       FIG. 4  is a left side elevation view of the fuel processing system of  FIG. 2 ; 
       FIG. 5  is an enlarged sectional side elevation view of the fuel processing chamber of the fuel processing system for turbine engines shown in  FIG. 2 ; and 
       FIG. 6  is a front view of a turbine engine apparatus with a plurality of fuel processing chambers, which form combustors, for a turbine engine. 
   

   DETAILED DESCRIPTION OF THE INVENTION 
   The present invention relates to a fuel processor for preparing fuel prior to introducing fuel into a combustor utilized in connection with a gas turbine engine. As mentioned, a gas turbine engine, according to the present invention, could be used in connection with jet airplanes, helicopters, turbo prop planes, land vehicles, ultralight planes, unlimited hydroplanes, military tanks, hovercraft, and any other suitable application. 
   With reference to  FIG. 1 , a typical gas turbine engine configuration utilizing a basic Brayton or Joule cycle characteristics is shown. It is well understood by those skilled in the art as to the basic operation of such a gas turbine engine. As shown, air enters into the compressor wherein the pressure of the air is increased. Pressurized air and fuel are thereafter introduced into the combustor, which burns the fuel and raises the temperature of the compressed air under constant-pressure conditions. The resulting high-temperature gases are then introduced to the engine where they expand and perform work. 
   The present invention relates to an apparatus for preparing fuel prior to allowing the fuel to enter into the combustion chamber. The fuel processing chamber may be a separate unit entirely upstream of the combustor, or alternatively, may be incorporated into the combustor unit. Irrespective of its precise configuration or assembly, the fuel processor prepares the fuel for combustion in connection with the operation of gas turbine engines. 
     FIG. 2  shows a fuel processing apparatus and system  10  for use in combination with a turbine engine. The fuel processor  10  includes a fuel inlet or fuel supply  12 , an initial fuel processor housing  14 , an initial fuel processor  16 , a secondary or main fuel processor housing  17 , and a main or secondary fuel processor  18 . Processed fuel then enters into the combustion chamber  20  where an igniter  21  ignites the atomized fuel from main processor  18  and fuel combustion results. The flame produced from fuel combustion is held within the flame holder  22 . Hot gases are allowed to escape the fuel processing system to impinge upon the blades of the turbine fan and perform the traditional work associated with turbine engines. 
   With reference more specifically to  FIGS. 4 and 5 , an initial fuel processing chamber  16  receives fuel from fuel inlet  12 . The fuel (represented by fuel flow arrow F) flows into a plurality of inlet openings  24  (see  FIG. 4 ) formed on the inlet end of the initial processing chamber. Alternatively, as shown in  FIG. 2 , the fuel inlet may be directly attached to the fuel processor  16  by extending inlet  12  to include a section or length  25  (shown in dashed lines) and thus the inlet apertures  24  would be eliminated. 
   Ambient air (represented by air flow arrow A) is allowed to enter into the main fuel processing chamber  16  by way of tangential apertures  26  formed in the wall  28  of the initial fuel processor  16 . Air entering into the initial fuel processor by way of tangential apertures  26  creates a vertical flow (i.e., a swirling, tornado-like flow) within the fuel processing chamber. The vertical flow causes the fuel/air mixture to impinge upon itself as the fuel-air spins within the fuel processing chamber  16 . This serves to break down and homogenize the fuel into an optimal fuel/air mixture for fast, efficient combustion. 
   To facilitate or enhance the flow of fuel into the fuel processing chamber  16 , a pair of cone-shaped members  30 ,  32 , are disposed in a back-to-back manner such that fuel F flowing from inlet  12  will pass around and be separated by initial cone  30 , will flow into apertures  24  ( FIG. 4 ) and ultimately into the fuel processing chamber  16 . As the fuel/air mixture passes down toward the downstream end of fuel processor  16 , it passes around adjacent cone  32  and toward a fuel outlet  33  (FIG.  5 ). It is to be understood that the cone-shaped members  30 ,  32  may be omitted from the fuel processor without departing from the scope of the present invention. In particular, where the fuel inlet  12  is attached directly to the fuel processor  16  (shown in dashed lines  25  in FIG.  2 ), cone  30  can be omitted as well as inlet apertures  24 . 
   After the fuel and air have mixed in the initial processing chamber  16 , fuel thereafter flows around a secondary cone-shaped member  34  and through inlet apertures  35  to the main or secondary fuel processor. Fuel thereafter enters into the main processing chamber  18 . As it enters into main processing chamber  18 , the air/fuel mixture is already experiencing a vortical flow and will rotate about cone-shaped member  34 . Additional ambient air A is also allowed to flow into the secondary or main processing chamber  18  by passing initially through apertures  41  in the housing and subsequently through exterior tangential apertures  42  which extend through the housing wall  40 . The initially processed fuel/air mixture is further processed in the primary fuel processing chamber  18 . The fuel is processed in the secondary or main fuel processing chambers  1   8  substantially the same as it is with respect to the initial fuel processing chamber  16 . Indeed, it is to be understood that one of the fuel processors may be utilized alone, without additional fuel processors. Alternatively, more than two fuel processors may be utilized in a series to achieve the desired fuel/air breakdown or homogenization. Ultimately, fuel passes through outlet  50  ( FIG. 5 ) and into the combustion chamber  20  ( FIG. 2 ) where an igniter  21 , such as a spark plug, ignites the processed fuel and a flame results, which is held by the flame holder  22 . Heat is allowed to escape via apertures  52  formed in the cone-shaped flame holder  22 . 
   The fuel/air mixture passing through outlet  50  of the main fuel processing chamber  18  is moving in a vortical flow. Thus, when the fuel/air mixture passes into the combustion chamber  20  (FIG.  2 ), the fuel/air mixture continues to flow in a vortical manner. This vortical flow enhances combustion for a more efficient use of the fuel to be utilized by the turbine engine. The vortical flow within the combustion chamber  20  ensures that the fuel/air mixture continues to be broken down or atomized to the appropriate degree, and that the fuel/air mixture is circulated within the combustion chamber  20  for complete combustion. 
   With reference to  FIG. 2 , the fuel processing apparatus and system  10  may be, in one embodiment, secured to a specialized housing  51  it which envelopes the entire fuel processing system  10 . A first flange  52  may be provide to allow the fuel processing system to be secured to any desired upstream mechanism, such as a compressor. A second flange  54  may be provided to secure the fuel processing system  10  to any appropriate downstream mechanism, such as a turbine. 
   With reference to  FIG. 6 , a turbine  60  is shown which is coupled in turn, to a plurality of fuel processing system housings  51  which hold, in turn, individual fuel processing systems  10 . The operation of the turbine  60  is conventional and will be known by those skilled in the art. By utilization of the plurality of novel fuel processors  10 , more efficient utilization of fuel results, and performances of the turbine  60  improves. 
   While this invention has been described with reference to certain specific embodiments and examples, it will be recognized by those skilled in the art that many variations are possible without departing from the scope and spirit of this invention. The invention, as described by the claims, is intended to cover all changes and modifications of the invention which do not depart from the spirit of the invention. The words “including” and “having,” as used in the specification, including the claims, shall have the same meaning as the word “comprising.”