Abstract:
A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft that is curved along its extent in leading to an air compressor in the gas turbine engine having a compressor air transfer duct extending therefrom to an internal combustion engine provided as an intermittent combustion engine at an air intake thereof. An inlet duct manifold is positioned against the duct wall of the inlet duct to cover a perforated portion thereof on the air compressor side of a curve therein with the inlet duct manifold having an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
       [0001]    Referenced herein are U.S. application Ser. No. 11/713,262 filed Mar. 2, 2007 for “COMBINATION ENGINES FOR AIRCRAFT” by Frederick M. Schwarz, Brian M. Fentress, Andrew P. Berryann, Charles E. Lents and Jorn A. Glahn; and U.S. application Ser. No. ______ filed on even date herewith for “AIRCRAFT COMBINATION ENGINES COMPLEMENTAL CONNECTION AND OPERATION” by Frederick M. Schwarz, Andrew P. Berryann and Brian M. Fentress. 
     
    
     BACKGROUND OF THE INVENTION 
       [0002]    The present invention relates to gas turbine engines for aircraft and, more particularly, to gas turbine engines each coupled to a corresponding auxiliary engine. 
         [0003]    Gas turbine engines as continuous combustion, open Brayton cycle internal combustion engines have come to dominate as the power plants for larger, faster aircraft to essentially the exclusion of reciprocating engines, or internal, intermittent combustion engines, earlier used as power plants for these kinds of aircraft. This is largely because of the greater power-to-weight ratio of gas turbine engines versus internal combustion engines, especially in large horsepower engines, or, more appropriately, large thrust engines in which those large thrusts are provided with a relatively small, and so smaller drag, frontal area engine structures relative to reciprocating engines. Gas turbine engines generate such large thrusts for propulsion, or horsepower for engines with an output shaft, by combining large volumes of air with large amounts of fuel, and thereby form a jet of large velocity leading to the capability to provide desired speedy flights. 
         [0004]    In addition to providing thrust, such gas turbine engines have operated integrated drive generators to generate electricity for the aircraft and for the engine electronic controls. The amount of electricity needed for these purposes in the past has tended to be relatively modest typically in the range of a few hundred kilowatts of electrical power but, with recently arriving new aircraft, exceeding a megawatt of power. However, there are some aircraft, usually for military uses, that have come to have needs for much larger amounts of electrical power either on a relative basis, the electrical power needed relative to the capability of the gas turbine engine available, or on an absolute basis with power needs significantly exceeding a megawatt. Furthermore, such demands for electrical power in military aircraft often occur at relatively high altitudes and often occur unevenly over relatively long time durations of use, that is, large peaks repeatedly occur in electrical power demand in the course of those long use durations. 
         [0005]    Corresponding attempts to obtain the added power from the typical aircraft propulsive system, the gas turbine engine, that are needed to operate the concomitant much larger capacity electrical generators, either on a relative or absolute basis, will subtract significantly from the thrust output of the available turbine or turbines. Making up that thrust loss in these circumstances by operating such available turbine engines so as to increase the thrust output thereof causes the already relatively low fuel use efficiency during flight to decrease significantly, which can severely limit the length of otherwise long duration uses, and also brings those engines closer to becoming operationally unstable. 
         [0006]    One alternative to using the gas turbine engine as the sole source of power to operate an electrical power generator is to add in the aircraft a further intermittent combustion internal combustion engine, such as gasoline engines operating on the any of the Diesel, Miller, Otto or Wankel cycles. Such engines can operate with a fuel efficiency on the order of seventy percent (70%) better than that of a continuous combustion (Brayton cycle) internal combustion gas turbine engine. At high altitudes, internal combustion engines of all kinds face the problem of limited power output because of the relatively small air pressures there limiting the chemical reactions of oxygen with hydrogen and oxygen with carbon in the burning the engine fuel in the engine combustion chamber or chambers. This can be solved for gas turbine engines by providing therein very large air flows through use, typically, of axial flow compressors usually in two stages with both a low compression compressor followed along the fluid flow path through the engine by a high compression compressor. This arrangement provides at least enough compressed air to the subsequent combustor to sustain the desired combustion process therein and a mass of airflow sufficient to combine with enough fuel to provide the energy needed to overcome the aircraft drag at the speed and altitude intended for operation. 
         [0007]    However, such compressors can provide considerably more compressed air than the minimum needed for this purpose thereby allowing some of this compressed air to be delivered through an air transport duct to the air intake of an intermittent combustion internal combustion engine so that, in effect, the compressors of the gas turbine engine serve as a very capable supercharger for that intermittent combustion engine. Thus, this intermittent combustion engine can be operated at the same relatively high altitudes at which the gas turbine engine propelling the aircraft operates while this turbine engine is also supplying compressed air to that intermittent combustion engine. There, depending on the values selected for the peak air intake pressure and engine compression ratio, the intermittent combustion engine can be used as a power source for an electrical power generator that can generate much greater amounts of electrical power than can one powered by a gas turbine engine. 
         [0008]    Some kinds of aircraft have the gas turbine engine used therein positioned within walls thereabout of a duct with the inlet side of that duct forming an inlet duct curved to follow a sinuous path to hide the front of that engine from impinging electromagnetic radiation at various wavelengths such as in a stealth type military aircraft (several kinds of which are unmanned aircraft). Typically, much of the inlet duct portion has a cross sectional area more closely approximating an elliptical shape rather than round so that the desired curves in the duct along its extent can be completed over a shorter extent distance, and then the duct cross section changes to being more round at the gas turbine engine location to accommodate that engine. The amount, or sharpness, of the curvature of the inlet portion of the duct, reflected in the curvature of the curve of cross sectional symmetry of that duct along its extent, resulting from the need to achieve the desired hiding of the front of the gas turbine engine depends on the space available for the duct in the aircraft and the size of that engine. That is, the length, L, of the duct curve of cross sectional symmetry from the duct opening to the atmosphere, on one end thereof, to the front of the gas turbine engine on the other end, and the diameter, D, of the front of that engine provide in their ratio L/D a parameter indicative of the curvature of the inlet portion of the duct, and so the compactness of this convoluted duct part and how extreme must be the resulting directional turning of airflows therethrough. 
         [0009]    Relatively slow aircraft speeds at which there is little ram effect forcing air into the inlet duct portion such as occur after takeoff of the aircraft from a runway, followed by relatively sharp climb angles with respect to the aircraft flight direction, and the like, lead to separation or separations of the air flows in this inlet duct from the walls of that duct at locations therein just past the relatively sharp curves occurring in this duct in the direction of extent thereof. Regions of such flow separations from the duct walls extending to the gas turbine engine can lead to stalling of the engine fan or cause individual fan blades to flutter and then structurally fail before the aircraft reaches speeds sufficient for the air entering the inlet duct portion to reach such ram pressures as to prevent these separations. Different ratios L/D for the inlet duct portion in aircraft having engines positioned in a duct will lead to different duct path turning angles and turning radii occurring therealong especially at those duct locations just before and past relatively sharp curves in the duct path. Air flow separations locations inwardly just past these curves will be less likely with less duct curvature along the duct path but reducing curvature may also negatively affect the positioning of the gas turbine engine in the aircraft. Thus, such duct curvature may nevertheless be required along with any of the likely air flow separations at these locations having to be tolerated thereby leading to a desire to prevent same. 
       BRIEF SUMMARY OF THE INVENTION 
       [0010]    The present invention provides a power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft open to the atmosphere and an inlet duct with a duct wall thereabout that is curved along its extent in extending from the air inlet along a curved path leading to an air compressor in the gas turbine engine followed therein by a combustor, the air compressor having a compressor air transfer duct extending therefrom so as to be capable of providing compressed air therein and to the combustor. In addition, there is in the aircraft an internal combustion engine provided as an intermittent combustion engine having an air intake coupled to combustion chambers therein, a rotatable output shaft also coupled to those combustion chambers for generating force, and a fuel system for providing fuel to those combustion chambers, the compressor air transfer duct being connected to the air intake to transfer compressed air thereto. An inlet duct manifold is positioned against the duct wall of the inlet duct to cover a perforated portion thereof on the air compressor side of a curve therein. The inlet duct manifold has an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake such that air can be selectively drawn from the inlet duct into the intermittent combustion engine air intake. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0011]      FIG. 1  is a schematic representation of a cross section side view of a portion of an aircraft embodying the present invention. 
       
    
    
     DETAILED DESCRIPTION 
       [0012]      FIG. 1  shows a schematic representation of a cross section side view of a portion of an aircraft with an example of such a gas turbine engine and intermittent combustion engine combination,  10 , in an arrangement in which most of the aircraft structure in which they are positioned has been omitted from this view. However, there is at least a portion of an engine duct,  11 , in that aircraft that is shown having openings, or perforations,  11 ′, in a portions of the walls thereof and further having an air inlet,  12 , facing forward in the aircraft. The configuration shown for duct  11 , with its somewhat sinuous shape, is from a stealth type military aircraft, several kinds of which are unmanned aircraft. This duct first curves downward, coming from the front of the aircraft at the duct opening provided by air inlet  12  to the atmosphere from which an airstream,  13 , is drawn. The duct then curves upward to open to a gas turbine engine provided as a turbofan engine,  14 , in engine duct  11  which uses airstream  13  for combustion and for fan forced air propulsion purposes. This passageway curvature of duct  11  past air inlet  12  serves to hide the front of engine  14  from impinging electromagnetic radiation at various wavelengths that could be reflected. Perforations  11 ′ are located primarily in the upper and lower portions of the duct wall just past the point of maximum curvature of the duct on the engine  14  side. Outer portions,  15 , of duct  11  adjacent engine  14  past a splitter convey the fan forced air provided by engine  14  for propulsion purposes into the remainder of duct  11  past engine  14  toward the outlet of duct  11  to the atmosphere as will be described below. 
         [0013]    This fan forced air and the combustion products resulting from combustion in engine  14  are forced out of the remainder of engine duct  11  to an exit nozzle,  16 , serving as the outlet of duct  11 . A fluid actuation system,  17 , provides the force to partial open and close nozzle  16  during the operation of turbofan engine  14 . Again, duct  11  past engine  14  first curves downward, coming from that engine, and then the duct curves upward to open to nozzle  16 . Here, too, this passageway curvature of duct  11  past engine  14  serves to hide the rear of engine  14  from electromagnetic radiation at various wavelengths impinging at the rear of the aircraft. 
         [0014]    Engine  14  has an air inlet guide vane,  20 , followed by a high pressure fan,  21 , as the fan for the turbofan engine to force air outside and past a splitter,  22 , and then through duct portions  15  into the rear of duct  11  and out of that duct through nozzle  16  to exit to the atmosphere. In addition, high pressure fan  21  also serves as a low pressure air compressor through delivering compressed air inside splitter  22  to a high pressure air compressor,  23 . The compressed air from high pressure compressor  23  arrives at a combustor,  24 , to which fuel is also delivered and burned. The combustion products form a jet of fluid which impinges first on a high pressure turbine,  25 , and then on a low pressure turbine,  26 , to cause them to rotate which, through appropriate mechanical linkings, leads to high pressure compressor  23  and high pressure fan  21  being forced thereby to also rotate. The combustion products then reach the remainder of duct  11  past engine  14  to exit through nozzle  16  to the atmosphere. 
         [0015]    A compressed air conveyance duct,  30 , is connected at one end into turbofan engine  14  to receive compressed air from high pressure compressor  23  through a compressed air flow control valve,  31 , typically controlled by a system computer (not shown but typically an engine control computer or an aircraft systems computer either eliminating the need for such an engine control computer or operating with it in a distributed control system), and used to control the flow of compressed air from high pressure compressor  23  through duct  30 . The opposite end of duct  30  is connected to an air intake, or intake manifold,  32 , leading to engine air intake valves,  33 , for an intermittent combustion engine,  34 , represented in the example of  FIG. 2  as a Diesel or Otto cycle engine. Intermittent combustion engine  34  is shown positioned forward in the aircraft of turbofan engine  14  to shift the center of mass of the aircraft forward to counter some of the weight of engine  14  but other positions are possible to be used if desired. 
         [0016]    Valves  33  in engine  34  control the air taken into combustion chambers,  35 , bounded by an engine block,  36 , providing the basic structure of engine  34  and by pistons,  37 . Each chamber also has an exhaust valve,  38 , through which combustion products are exhausted to an exhaust manifold,  39 . A rotatable crankshaft,  40 , has a connecting rod,  41 , rotatably coupling it to a corresponding one of each of pistons  37 . A rotatable camshaft,  42 , is used to open and close air intake valves  33  and exhaust valves  38  in a suitable sequence. 
         [0017]    Crankshaft  40 , under the control of a system controller not shown, is rotated by the force on pistons  37  transmitted thereto by corresponding ones of connecting rods  41  due to repeated combustion events in the corresponding combustion chamber  35  which events occur in all of chambers  35  in a suitable sequence before repeating. These events correspondingly use the air quantities taken through valves  33  repeatedly into, and the fuel quantities repeatedly injected into, those chambers for combustion. The fuel quantities are injected by a fuel injection system not seeable in this figure and the magnitudes thereof are used to select the mechanical power output of crankshaft  40  of the intermittent combustion engine. The resulting combustion products are correspondingly repeatedly rejected from those chambers through valves  38 . If an Otto cycle engine is used as intermittent combustion engine  34 , the combustion events are initiated by the repeated sparkings of spark plugs not shown in this figure in a suitable sequence across combustion chambers  35  under the control of the system controller. In addition, intermittent combustion engine  34  has a cooling system not shown for cooling the engine structure about combustion chambers  35 . 
         [0018]    The rotation of crankshaft  40  is suitably fastened to an input shaft,  43 , of a primary electrical power generator,  44 . The resulting rotation of input shaft  43  electrically energizes output electrical conductors,  45 , of generator  44  to thereby generate the desired electrical power thereat for operating aircraft devices (not or not all shown). The demand for electrical power in the aircraft is used as a basis to select the fuel quantities injected in the combustion chambers of the intermittent combustion engine to have that engine supply sufficient mechanical power crankshaft  40  to sufficiently rotate input shaft  43  of generator  44  to meet that demand. 
         [0019]    An exhaust duct,  46 , extends from exhaust manifold  39  of intermittent combustion engine  34  to an exhaust turbine,  47 , to result in the combustion products of engine  34  impinging on the blades of that turbine to thereby cause it to rotate. A central shaft of this exhaust turbine is coupled to an input shaft of a secondary electrical power generator,  48 . The resulting rotation of this input shaft electrically energizes output electrical terminals,  49 , of generator  48  to thereby generate the further desired electrical power thereat. 
         [0020]    Another supplemental electrical power generator is provided in this example by operating an electrical starter (generator),  50 , with the electrical motor therein operated also as an electrical generator after the completion of the starting process. Starter (generator)  50  rotates high pressure air compressor  23  to start turbofan engine  14  and, thereafter, with engine  14  operating, this compressor can selectively rotate the rotor in starter (generator)  50  to cause the starter motor to be operated as an electrical power generator. 
         [0021]    Starter (generator)  50  has drive (input) shaft,  51 , extending from the rotor therein to a set of bevel gears,  52 , with the bevel gear on the opposite side of this set rotatably coupled to a clutch,  53 . Clutch  53  allows the system computer to engage and disengage starter (generator)  50  as appropriate. The opposite side of clutch  53  has an engagement shaft,  54 , extending therefrom ending in bevel gear rotatably engaged with a counterpart bevel gear in a portion of high pressure air compressor  23 . 
         [0022]    A further supplemental electrical power generator,  55 , is shown in  FIG. 1  for this example which has an input shaft,  56 , extending from the rotor therein to a set of bevel gears,  57 , with the bevel gear on the opposite side of this set rotatably coupled to a shaft,  58 , which in turn is coupled to a further set of bevel gears,  59 . These bevel gears are coupled to an output shaft of low pressure turbine  26  through a clutch,  60 . Clutch  60 , here too, allows the system computer to engage and disengage generator  55  as appropriate. 
         [0023]    During takeoff from a runway of an aircraft containing turbofan engine  14  and intermittent combustion engine  34  and the following climb to gain altitude, intermittent combustion engine  34  is unlikely to be needed to provide torque to electrical generators  44  and  48  for the purpose of their generating large amounts of electrical power while still near that runway. In this portion of the flight, relatively slow aircraft speeds occur leading to the result that air is not forced with substantial pressure into inlet  12  of the inlet portion of duct  11 . In this circumstance, often compounded by the relatively sharp climb angles with respect to the aircraft flight direction used after takeoff to gain altitude, separation or separations can occur of the air flows in this inlet duct from the walls of that duct at locations therein just past the relatively sharp curves provided in this duct. Except for possibly being used to start turbofan engine  14 , intermittent combustion engine  34  is available in at least this part of the flight to aid in preventing such separations without having to be sized sufficiently to both provide such aid and to provide torque to electrical generators. This engine can do so by establishing a reduced pressure at these locations during this part of the flight by drawing air through perforations  11 ′ located there to help force the duct flows to remain flowing along these portions of the duct walls. 
         [0024]    In the distribution of perforations  11 ′ in the walls of the inlet portion of duct  11  for this purpose on the turbofan engine side of the location of the major curve in the path followed by that duct, the greatest densities of those perforations are provided in the walls of the duct at the intersections of duct  11  and a plane projected there through the centerline of that duct. This plane is oriented such that those intersections have the greatest curvature out of those among the various possible intersections. In  FIG. 1 , those are the portions of duct  11  at the top and bottom thereof on the engine  14  side of the curves in that duct as it is curving along its path in the plane of that figure as this is where flow separations are most likely to occur. The density of perforations  11 ′ diminishes at locations away from the top and bottom locations of maximum perforation densities along peripheral paths over sides of duct  11  between the maximum perforation density locations. 
         [0025]    Thus, in  FIG. 1 , to enable intermittent combustion engine  34  to reduce pressure at the locations of these perforations  11 ′, a partially cut away manifold,  70 , is provided shown girdling the input portion of duct  11  so as to be more or less sealed to that duct such that perforations  11 ′ all open from the inside of the duct to the space enclosed by manifold  70  in being sealed to the inlet portion of duct  11 . The sealing of manifold  70  to the inlet portion of duct  11  is provided at flanges,  71 , extending at the sides of manifold  70  parallel to the outer surface of the duct walls adjacent thereto with a suitable sealing and fastening means. An inlet draw duct,  72 , extends at its inlet end from manifold  70  to a flared output end thereof provided adjacent to the fluid drawing side of a blower,  73 . 
         [0026]    The rotor in blower  73  on which the blower blades are mounted is selectively rotated by intermittent combustion engine  34  through an extension shaft,  74 , suitably fastened to crankshaft  40  that engine. Extension shaft  74  is coupled to the blower rotor through a clutch, allowing this rotor to be disengaged from engine  34  under control of the system computer when the blower is not needed, and then through a pair of bevel gears,  76 , to increase the rotational speed of the rotor beyond that of crankshaft  40 . The air flow through blower  73 , either when the rotor thereof is being rotated by engine  34  or not, is received in the flared input end of a coupling duct,  77 , in which it is conveyed through a backflow elimination valve,  78 , when open to emerge at the output end of duct  77  where it merges with compressed air conveyance duct  30  just ahead of its connection to air intake, or intake manifold,  32  of intermittent combustion engine  34 . However, when compressed air from high pressure compressor  23  is selected to be provided through compressed air flow control valve  31  from high pressure compressor  23  through duct  30  to intake manifold  32  of engine  34 , valve  78  is closed to prevent that compressed air from being forced through perforations  11 ′ into the inlet portion of duct  11 . 
         [0027]    The magnitude of the required air flow through perforations  11 ′ from the inlet portion of duct  11  can in some circumstances be as large as 3 to 5% of the total airflow through turbofan engine  14 , and this is why blower  73  is provided to supplement the airflow through intake manifold  32  that results from just operating intermittent combustion engine  34  alone. The system computer receives information from appropriate aircraft and engine sensors (not shown) such as the input and output pressure ratio of high pressure compressor  23  or its rotor rotational speed as an indicator of the power being delivered by turbofan engine  14 , air temperature, altitude, climbing or descending aircraft angle of attack, or landing gear being down as an indication of an imminent change in the descending angle of attack. From such information, the system computer determines the need for drawing air through perforations  11 ′ from the inlet portion of duct  11  to prevent flow separations from the walls of the inlet portion of that duct past its major curve, and the magnitude thereof needed. 
         [0028]    Thus, the system computer can determine that the airflow through intake manifold  32  that results from operating engine intermittent combustion engine  34  alone is sufficient at some operational rotational rate of that engine which the computer selects by controlling the amount of fuel supplied to be injected by the fuel injection system (not shown) for that engine. If the system computer determines that the maximum practical airflow through perforations  11 ′ forced in this manner is insufficient, that computer causes clutch  75  to engage blower  73  to substantially increase that airflow. If the resulting airflow is greater than can be accommodated by the air intake through intake manifold  32 , engine air intake valves  33 , combustion chambers  35 , exhaust valves  38 , and exhaust manifold  39 , a relief duct,  79 , extending from intake manifold  32  conveys the excess through a relief valve,  80 , which is caused to be opened by the system computer after determining such a condition exists. This excess airflow is then vented thereby to the atmosphere. Although not shown, the output side of relief valve  80 , rather than merely venting the excess airflow to the atmosphere, could be connected by a duct to a variable opening nozzle controlled by the system computer to result in the excess airflow providing additional thrust for the aircraft. 
         [0029]    Although the present invention has been described with reference to preferred embodiments, workers skilled in the art will recognize that changes may be made in form and detail without departing from the spirit and scope of the invention.