Abstract:
This invention is a fuel injection control system for a turbine engine. The invention uses at least one fuel injector, having means for injecting fuel in pulses to the combustion chamber of a turbine engine, and an electronic control unit to receive and interpret input sensor signals from selected operating functions of the engine and to generate and direct fuel injection signals to modify the pulse duration and/or frequency of fuel injection in response to a deviation from a selected operating function, such as the desired operating speed, caused by variable operating loads encountered by the turbine engine. This configuration provides significantly greater fuel efficiency, better operational control and response time, and a lighter weight than is currently available in turbine engines. The invention may be used in many applications such as commercial, private, experimental and military aviation, power plant turbines, and other industrial, military and mining applications.

Description:
TECHNICAL FIELD  
         [0001]    This invention relates to a fuel injection control system for turbine engines that can be used in many different applications such as jet and turboprop engines used in commercial, private, experimental and military aviation, power plant turbines, and other industrial and mining applications for turbine engines. Injectors inject fuel into the combustion chamber of a turbine engine. An electronic control unit, pulse width modulation system governs the injection duration and/or frequency of the pulsed fuel, providing precise operational control over a very broad range of operating conditions. The control system thus provides significantly better fuel efficiency, lighter weight, and better engine operational control than is currently available in turbine engines.  
         BACKGROUND OF THE INVENTION  
         [0002]    Conventional turbine engines used in most applications, including aviation, power generation, and industrial applications, generally have a combustion chamber, in which fuel is combusted in the presence of air to produce exhaust gas which drives a series of gears/shafts and ultimately the driven load (such as a propeller, fan or blades of the turbine engine, a pump, a generator, or a speed conversion unit) depending upon the application, and a continuous-stream fuel delivery system (such as a valve or nozzle), which delivers fuel to the combustion chamber for combustion. These fuel delivery systems generally introduce fuel in a continuous stream into the combustion chamber, and are usually controlled by mechanical means that sense and respond to changing pressure, vacuum, or other physical or mechanical inputs within the system.  
           [0003]    Conventional fuel delivery systems for turbine engines also rely on any of several physical processes to break the continuous fuel stream into fuel droplets or a mist for combustion to take advantage of the well-known inverse relationship between the size of a fuel droplet and the efficiency of combustion. The smaller the fuel particle, the greater the rate and efficiency of combustion. Engineers and scientists have experimented with fuel nozzle design for many years to maximize the efficiency of combustion. Examples include U.S. Pat. No. 5,603,211 (“Outer Shear Layer Swirl Mixer for a Combustor”) and U.S. Pat. No. 5,966,937 (“Radial Inlet Swirler with Twisted Vanes for Fuel Injector”). Typical “break-up” processes include the use of physical barriers against which fuel is directed to spatter it into droplets; the use of “swirlers,” “slingers” or other centrifugal force generators which sling fuel against the wall of a combustion chamber to break up a continuous fuel stream using mechanical means; and the use of high velocity air streams to fractionate a continuous fuel stream. Thus, the object of the modern design of turbine fuel delivery systems is to employ a process to break up a continuous stream of fuel droplets or to atomize the fuel. An object of this invention is to supplement the mechanical breakup of fuel by pulsing the fuel stream into the combustion chamber.  
           [0004]    Turbine engines as described above suffer from several significant limitations that relate to continuous-stream, mechanical-control delivery systems. These limitations include at least the following: (1) fuel combustion is less efficient than it would be if fuel would be introduced into the combustion chamber in droplets rather than via a continuous stream; (2) there may be inefficient fuel distribution throughout the combustion chamber, which contributes to the inefficiency of combustion; (3) the exhaust gas often contains unburned fuel, which may contribute to air pollution; (4) the control systems often do not permit the operator control the fuel delivery process in relation to important operating variables (such as flow rate, air consumption rate, load changes, etc) as precisely as may be desired; (5) the systems can be difficult to operate and maintain; (6) the control system can be complex because of many moving parts; (7) the systems can add unwanted weight to the turbine, which is particularly problematic in aviation applications; and (8) the delivery and control systems can be expensive to manufacture and/or assemble because of their complexity and close mechanical tolerances; and (9) the response time is inherently slow because it is a mechanical system.  
           [0005]    This invention is designed to overcome these limitations through two principal features. First, fuel is injected into the combustion chamber in pulses, using a fuel injector, rather than in a continuous-stream delivery system. This feature offers the distinct advantage of atomizing the fuel and delivering it in pulses into the combustion chamber in a fine mist or even a vapor, and thereby eliminates the need to employ a physical process to break up a continuous fuel stream. The fuel is combusted more efficiently because the invention reduces the size of the individual fuel cells that are being burned. Fuel injectors are commonly used for this purpose in internal combustion engines (see, e.g., U.S. Pat. No. 6,279,841 (“Fuel Injection Valve”) and U.S. Pat. No. 6,260,547 (“Apparatus and Method for Improving the Performance of a Motor Vehicle Internal Combustion Method”)) but have not been used to inject fuel pulses in turbine engines. Second, the invention uses an electronic control unit that detects sensor signals from chosen operating functions of the engine and then modifies the duration and/or frequency of fuel pulses that are injected into the combustion chamber. This control system thus provides precise operational control over a very broad range of operating conditions.  
           [0006]    The combination of these features in the invention yields a fuel injection control system for a turbine engine that makes the engine more efficient, lighter, easier to operate and maintain, and more responsive than is currently available. In an aviation application, obviously any reduction in the weight of the turbine engine benefits the overall performance and fuel efficiency of the craft.  
         SUMMARY OF THE INVENTION  
         [0007]    This invention is an apparatus and method for controlling the injection of fuel in a turbine engine having a combustion chamber. The apparatus comprises at least one fuel injector having means for delivering fuel in pulses to said combustion chamber of said turbine engine; at least one operating sensor, said sensor having means for receiving sensor signals from a selected operating function of said turbine engine; a programmable electronic control unit for receiving and comparing the value of said sensor signals from said turbine engine to the value of a desired signal, and for generating fuel injector control signals in response thereto; and a means for directing said fuel injector control signals to said fuel injector to modify the pulse duration and/or frequency of fuel injection in response to a deviation from a selected operating function, such as the desired engine speed, caused by variable operating loads encountered by the turbine engine. The method for controlling the injection of fuel in a turbine engine having a combustion chamber and having at least one fuel injector and at least one sensor for sensing operating signals from said engine comprises the steps delivering fuel in pulses to said combustion chamber using said injector; sensing at least one operating sensor signal from said turbine engine using said sensor; directing sensor signals from said operating sensor to a programmable electronic control unit; at said programmable electronic control unit, comparing the value of said sensor signal to the value of a desired signal and generating fuel injector control signals in response to said sensor signal; and directing said fuel injector signals to said fuel injector to modify the pulse duration and/or frequency of fuel injection in response to a deviation from desired engine speeds caused by variable operating loads encountered by the turbine engine. 
       
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0008]    [0008]FIG. 1 is a diagram of a hypothetical, typical control panel for the turbine engine of a turbo-prop airplane  
         [0009]    [0009]FIG. 2 is a schematic representation of a fuel injector projecting into the combustion chamber of a turbine engine and connected to the engine&#39;s control panel.  
         [0010]    [0010]FIG. 2 a  is a side view of a typical fuel injector.  
         [0011]    [0011]FIG. 3 is a block diagram showing the relationship among the turbine engine sensors, electronic control unit and fuel injector.  
         [0012]    [0012]FIG. 4 is a block diagram showing the use of engine speed, measured as revolutions per minute, and exhaust gas temperature, measured using an exhaust gas temperature probe, as turbine engine sensors to generate sensor signals which are conveyed to the electronic control unit.  
         [0013]    [0013]FIG. 5 is a schematic representation of a configuration of integrated circuits on the electronic control unit.  
         [0014]    [0014]FIG. 6 is a block diagram showing the operating steps of the fuel injection control system. 
     
    
     DETAILED DESCRIPTION OF THE INVENTION  
       [0015]    Referring now to the figures, FIG. 1 is a diagram of a hypothetical but typical control panel for a turbine engine of a turboprop airplane, which is one possible application for the invention and is the embodiment described herein. However, there are many applications for the invention; this is just one of its many potential applications to turbine engines. In the embodiment illustrated here, a typical control panel  100  contains instrument gauges for exhaust gas temperature  1 , propeller pitch  2 , amps  3  and volts  4 . The panel may also contain other gauges for other relevant parameters such as fuel level, oil pressure, air speed, altitude, etc., all of which have been omitted here. The hypothetical control panel  100  illustrated in FIG. 1 contains digital displays for engine revolutions per minute (RPM)  5  and operating hours  6 . It also contains toggle switches for the main switch  7 , spark start solenoid  8 , fuel computer  9 , starter  10 , and propeller pitch  11 . The panel has manual control dial  12  and automatic control dial  13  for operating the fuel injection control system, and control switch  15  for switching between manual and automatic operation. Control dials  12  and  13  are connected to electronic control unit (ECU)  14 , which in this application does not sit on control panel  100 . ECU  14  can be located at any desired place on the engine. ECU  14  functions as a pulse width modulation control system for the fuel injectors, as shown in FIGS. 5 and 6 and described below. The ECU may take any of several forms, including solid state circuitry, a microprocessor and a microcomputer.  
         [0016]    [0016]FIG. 2 is a schematic illustration of a fuel injector projecting into the combustion chamber of a turbine engine. FIG. 2 a  is a side view of a typical fuel injector. Various types of fuel injectors are known for use in internal combustion engines such as automobile engines. They are available commercially from any of several manufacturers (e.g., Ford Motor Company, Robert Bosch GmbH) as off-the-shelf items. The novelty of this invention consists, in part, in adapting a fuel injector and employing sensors and ECUs for turbine engine use. The size and number of injectors used in any particular application will depend on the size of the engine, the size of the combustion chamber, the desired horsepower output, and similar factors. Many applications, including the aircraft embodiment described herein, will commonly employ from 4 to 8 fuel injectors. However, any turbine engine to which this invention applies will have at least one fuel injector having a means for delivering fuel in pulses into a combustion chamber. The injectors may be connected by a common fuel line (such as a fuel rail) or may have independent lines as desired. A fuel pump may be used to pump fuel into the fuel line. Conceivably, the electronic control unit could be integrated with the fuel pump as an additional or alternate way to control fuel injecting into the combustion chamber.  
         [0017]    As shown in FIGS. 2 and 2 a , a typical injector  20  has a fuel inlet port  22  which receives fuel from a fuel tank or other supply source, a fuel injection port  21 , and a control port  23 . In the embodiment illustrated in FIG. 2, fuel is distributed to fuel inlet port  22  of the fuel injector through a fuel rail  25 . Preferably, each injector should be positioned so that its fuel injection port  21  protrudes into combustion chamber  24  of the turbine engine. Wiring or other appropriate means of directing injector signals from the ECU to the fuel injector (as described below) is connected with the fuel injector  20  through control port  23 . This arrangement allows injector  20  to inject pulses of fuel through injector port  21 , in response to fuel injector signals directed into control port  23  from ECU  14 , directly into combustion chamber  24 , where the fuel pulses can be burned in the presence of air in the chamber. Exhaust gases from combustion in the combustion chamber are exhausted through an exhaust cone  26  or similar structure, as depicted in FIG. 2.  
         [0018]    It is helpful to generally describe how a fuel injector functions before describing how this invention&#39;s control system integrates with the fuel injector(s) to control fuel injection in response to a deviation from desired operating speeds caused by variable operating loads encountered by the engine. Fuel injectors commonly have an electrically controlled or electromagnetically actuated valve that regulates the flow of fuel through the injector. A valve-closure member (or plunger)  27  typically presses against a valve seat  26  in the closing direction when the magnetic coil  28  is not excited. When the coil is excited, the valve-closure member releases from the valve seat in the open direction. Thus the injector valve opens and closes at desired intervals in response to an electrical stimulus to the injector&#39;s electromagnet, thereby delivering a desired amount of fuel (usually measured in milligrams) per given period of time (usually measured in milliseconds) through the injector into the combustion chamber. The injector nozzle (not shown on the drawings) is designed to atomize the fuel or to make as fine a fuel mist as is possible so that the fuel bums easily.  
         [0019]    A cycle of valve operation is defined as a given period of time during which the valve has both open and closed phases. The flow of fuel through an injector is generally governed by two variables, pulse width and frequency. Pulse width refers to the length of time (measured typically in milliseconds) that the valve is open during one complete cycle of valve operation. For example, a greater pulse width means that the valve is open relatively longer than it is for a shorter pulse width during a given cycle. A greater pulse width allows more fuel to pass through the injector than a shorter pulse width. Frequency refers to the spacing between valve cycles. The term “pulse width modulator” (PWM) refers to the ability to control pulse width during a given frequency.  
         [0020]    [0020]FIGS. 3 and 4 are simplified diagrammatic overview representations of the best mode of how the control system functions to control the duration and/or frequency of fuel pulsing into the combustion chamber. The control system comprises one or more sensors that track selected engine operating functions (such as engine speed, engine power, engine fuel demand, or other function(s)) to determine how well the engine is performing as compared to a desired condition or set point; a group of inputs into ECU  14 ; a programmable memory device such as one or more integrated circuits, or computer chips, which comprise ECU  14  itself; and a group of outputs from ECU  14  that control fuel injection into the combustion chamber. As illustrated in FIG. 3, turbine engine sensors  41  sense deviations in the selected operating function in response to various demands placed on the engine. The selected operating function can be either static or dynamic i.e., the operating function “set point” may stay constant or vary as the engine operates. In this embodiment, turbine engine sensors  41  sense deviations in operating speed resulting from variable operating loads (i.e., increasing the load decreases engine operating speed) and generate electric sensor signals  42 , which function as the inputs to ECU  14 . The outputs from ECU  14  are electric fuel injector control signals  43  that pass to control port  23  of fuel injector  20  to regulate the pulse duration and/or frequency of fuel pulsing through injector port  21  into combustion chamber  24 . ECU  14  conceivably can be programmed to generate fuel injector signals  43  that modify the ratio of pulse duration to frequency of the fuel injector in response to a deviation from desired operating speeds  
         [0021]    In the embodiment illustrated here (i.e., employing the fuel injection control system to control operating speed of a turbo-prop airplane), the selected turbine engine sensor inputs  41  to ECU  14  are the revolutions per minute (RPM) of the output shaft and the temperature of the exhaust gas, as depicted in FIG. 4. A wide variety of other input signals, such as oxygen content of the exhaust gas, mass airflow into the engine, engine temperature, and driven load (including but not limited to propeller pitch, generator load, and fluid power loads) may be used as appropriate, depending on the application. As shown in FIG. 4, the turbine engine is fitted with engine speed sensor  45  and with an exhaust gas temperature sensor  47  to detect the RPMs and exhaust gas temperature, respectively, of the engine as the engine responds to differing loads it encounters. These sensors can be conventional devices for monitoring these functions, such as a tachometer and a thermocouple temperature probe. Engine speed sensor  45  generates an electric RPM signal  46  that is conveyed to ECU  14  by an appropriate means such as conventional wiring. Likewise, exhaust gas temperature sensor  47  generates an electric temperature signal  48  that is also conveyed to ECU  14  by an appropriate means. ECU  14  then generates fuel injector control signals  43  that are conveyed to fuel injector  20  to control the duration and/or frequency of fuel passing through the injector in response to variations in the input signals, as discussed below.  
         [0022]    ECU  14  comprises a group of integrated circuits that receives input signals and generates output signals as shown in FIG. 5. ECU  14  may be programmed with integrated circuits as desired. In this embodiment, the input signals are operator inputs from control dials  12  and  13 , and RPM signal  46  and temperature signal  48  from the engine. The output signals are fuel injector control signals  43  to the control ports  23  of fuel injectors  20  and an output to RPM display  5  on control panel  100 . FIGS. 5 and 6 together illustrate how ECU  14  functions.  
         [0023]    The operator first selects manual mode by switching control switch  15  to activate manual control dial  12  on control panel  100 , engages starter  10 , and turns on spark start solenoid switch  8  to cause the turbine to begin to rotate. The operator then turns on fuel computer switch  9  to cause the engine&#39;s battery to deliver an electric current to the selected number of system power supply integrated circuits which are located on ECU  14 , as illustrated in FIG. 5. The embodiment shown here has three such power supply integrated circuits. Manual control power supply integrated circuit  51  regulates the power provided by the engine&#39;s battery to a uniform voltage and supplies it to the manual control portion of the unit. Automatic control power supply integrated circuit  52  regulates and supplies power to the automatic control portion of the unit. Digital control power supply integrated circuit  53  regulates and supplies power to digital RPM display  5  on control panel  100 .  
         [0024]    The operator next selects a desired pulse duration by rotating manual control dial  12 , which transmits a signal to manual pulse forming integrated circuit  54  on ECU  14 , as shown in FIGS. 5 and 6. Manual pulse forming integrated circuit  54  interprets this command signal and generates positive going pulses at a preset frequency in proportion to the supplied signal. These pulses are then directed to amplification system integrated circuit  55  on ECU  14 . The pulses amplified by amplification system integrated circuit  55  become the fuel injector control signals  43  that are conveyed to engine injectors  20 , which in turn open when the pulse is present and close in its absence to deliver fuel to the engine. Thus, the width (or duration) of the pulse controls the amount of fuel admitted through each injector.  
         [0025]    The fuel entering combustion chamber  24  of the engine is ignited, and the resultant expansion of the combustion gases causes the turbine to begin to rotate at a given speed. As the operator increases manual control dial  12 , an increased signal is sent to manual pulse forming integrated circuit  54 , which causes an increase in the pulse width generated by manual pulse forming integrated circuit  54  and amplified by amplification system integrated circuit  55 . The longer duration pulses amplified by amplification system integrated circuit  55  cause engine injectors  20  to remain open longer, thus delivering more fuel and increasing engine speed (RPM).  
         [0026]    Upon reaching a minimum sustainable speed, the operator now switches over to automatic mode by switching control switch  15  to activate automatic control dial  13  on control panel  100 . This control generates a signal that is directed to integrating amplifier integrated circuit  56  on ECU  14  (FIG. 5). The engine&#39;s electrical system alternator functions as engine speed sensor  45  by generating a frequency in proportion to its rotational speed. This frequency is directed to voltage converter integrated circuit  57 , where it is converted to a DC voltage that is directly proportional to the supplied frequency, thus providing the operator an input of turbine shaft speed. The output of voltage converter integrated circuit  57  is split into two signals. One signal is directed to analog-to-digital integrated circuit  60  that measures the voltage and encodes it to illuminate the correct segments of digital RPM display  5  on control panel  100  to provide a visual indication of engine RPM. The other signal is directed to operational amplifier integrated circuit  58  on ECU  14 , where it is electrically isolated and passed along to integrating amplifier integrated circuit  56 .  
         [0027]    Integrating amplifier integrated circuit  56  now compares the desired RPM signal discussed above with the scaled and isolated signal introduced by operational amplifier integrated circuit  58 , and creates an output voltage in relation to the error between the requested RPM and the actual RPM. This output voltage increases over time if the actual RPM is below the requested RPM and decreases over time if the actual RPM is above the requested RPM. The rate of change is related to the amount of error as a continuously integrated function.  
         [0028]    This control signal is now directed to automatic pulse forming integrated circuit  59 , which interprets this command signal and generates positive going pulses at a preset frequency in proportion to the amount of signal supplied. These pulses are then directed to amplification system integrated circuit  55 . Electric pulses amplified by amplification system integrated circuit  55  become fuel injector control signals  43  that are conveyed to engine injectors  20 . These signals cause the injectors to open when the signal is present to deliver fuel to the engine and to close in its absence to halt fuel delivery. Thus, the width (or duration) if the electric pulse controls the amount of fuel admitted through each injector  20 .  
         [0029]    Engine speed sensor  45  will detect decreased engine speed (RPM) caused by increased loading on the engine and will send RPM sensor signal  46  to voltage converter integrating circuit  57  on ECU  14 . The engine alternator and the ECU feedback system chain of voltage converter integrated circuit  57 , operational amplifier integrated circuit  58 , and integrating amplifier integrated circuit  56  modifies the input to automatic pulse forming integrated circuit  59  and to amplification system integrated circuit  55 , sending fuel injector signals  43  to the injectors  20  thereby causing them to remain open for a longer time to inject more fuel to maintain the desired RPM. The same but opposite effect occurs upon decreasing load on the engine. Reaction time of the system is measured in milliseconds, and provides an almost instantaneous correction to load-induced RPM variations.  
         [0030]    A second input to the control system in this embodiment is a constant monitoring of exhaust gas temperature to protect the structural integrity of the engine. A thermocouple may be inserted into the exhaust gas stream to act as exhaust gas temperature sensor  47 . This sensor monitors exhaust gas temperature and generates a minute electrical voltage due to the Seebeck effect, which is proportional to gas temperature. This electrical temperature signal  48  is directed to thermocouple amplifier integrated circuit  61  located on ECU  14  (FIGS. 5 and 6), where it is amplified by a factor of 100. The electrical output of thermocouple amplifier integrated circuit  61  is directed to voltage comparator integrated circuit  62 , where it is compared to a preset voltage chosen to reflect a maximum safe operating temperature of the turbine components. The output of comparator integrated circuit  62  is directed to the input of integrating amplifier integrated circuit  56  to meet the already present RPM demand signal previously discussed. When exhaust gas temperature rises to the preset safety level, thermocouple amplifier integrated circuit  61  and comparator integrated circuit  62  generate an output signal to cause an override to the incoming signal from automatic control dial  13 , artificially forcing the RPM demand signal to a lower level and thereby causing a reduction in the signal to automatic pulse forming integrated circuit  59  and amplification system integrated circuit  55 . This reduced fuel injector control signal  43  decreases the duration of fuel pulsing through injectors  20  by way of the feedback loop discussed above. The resultant decrease in delivered fuel slows the engine, reduces exhaust gas temperature, and protects the turbine components.