Abstract

A crankshaft detection system includes a pickup element mounted to an end of a crankshaft and disposed within a rear portion of the aircraft engine's crankcase. The crankshaft detection system also includes pickup element sensor secured to a mounting location formed in the rear portion of the aircraft engine's crankcase and disposed in proximity to the pickup element. As the crankshaft rotates the pickup element relative to the pickup element sensor, the pickup element causes the pickup element sensor to generate a signal indicative of the angular velocity and rotational position of the crankshaft. In order to optimize engine performance, in response to the signal, the controller controls a spark event associated with each the cylinder assembly of the engine such that ignition of the fuel and air mixture occurs within each cylinder assembly at a time prior to each piston of each cylinder assembly reaching a top dead center position.

IPC Classes  ?

• F02P 7/067 - Electromagnetic pick-up devices

Abstract

An aircraft engine includes an aircraft engine controller configured to detect an actual peak exhaust gas temperature of a cylinder assembly. The aircraft engine controller detects an intersection between a first function representing a relationship between a set of rich exhaust gas temperature signals and a corresponding set of rich fuel-air ratio values and a second function representing a relationship between a set of lean exhaust gas temperature signals and a set of lean fuel-air ratio values. Based upon the intersection between the first and second functions, the engine controller detects an actual peak fuel-air ratio value for the cylinder assembly and can determine if a correction in the fuel-air ratio of a fuel-air mixture provided to the cylinder assembly is required.

IPC Classes  ?

• F02D 41/14 - Introducing closed-loop corrections

Abstract

An aircraft engine includes an aircraft engine controller configured to detect an actual peak exhaust gas temperature of a cylinder assembly. The aircraft engine controller detects an intersection between a first function representing a relationship between a set of rich exhaust gas temperature signals and a corresponding set of rich fuel-air ratio values and a second function representing a relationship between a set of lean exhaust gas temperature signals and a set of lean fuel-air ratio values. Based upon the intersection between the first and second functions, the engine controller detects an actual peak fuel-air ratio value for the cylinder assembly and can determine if a correction in the fuel-air ratio of a fuel-air mixture provided to the cylinder assembly is required. Accordingly, the engine controller provides each cylinder assembly of the aircraft engine with an accurate fuel-air mixture to allow for operation of the engine with optimal fuel economy.

IPC Classes  ?

• F02B 23/00 - Other engines characterised by special shape or construction of combustion chambers to improve operation
• B60T 7/12 - Brake-action initiating means for automatic initiationBrake-action initiating means for initiation not subject to will of driver or passenger

Abstract

An aircraft engine includes an aircraft engine controller configured to detect an actual peak exhaust gas temperature of a cylinder assembly. The aircraft engine controller detects an intersection between a first function representing a relationship between a set of rich exhaust gas temperature signals and a corresponding set of rich fuel-air ratio values and a second function representing a relationship between a set of lean exhaust gas temperature signals and a set of lean fuel-air ratio values. Based upon the intersection between the first and second functions, the engine controller detects an actual peak fuel-air ratio value for the cylinder assembly and can determine if a correction in the fuel-air ratio of a fuel-air mixture provided to the cylinder assembly is required.

IPC Classes  ?

• F02D 41/14 - Introducing closed-loop corrections

Abstract

One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.

IPC Classes  ?

• G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration

Abstract

One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.

IPC Classes  ?

• G05B 23/02 - Electric testing or monitoring

Abstract

A crankshaft detection system includes a pickup element mounted to an end of a crankshaft and disposed within a rear portion of the aircraft engine's crankcase. The crankshaft detection system includes a pickup element sensor secured to a mounting location formed in the rear portion of the crankcase and disposed in proximity to the pickup element. As the crankshaft rotates the pickup element relative to the pickup element sensor, the pickup element causes the pickup element sensor to generate a signal indicative of the angular velocity and rotational position of the crankshaft. In order to optimize engine performance, in response to the signal, the controller controls a spark event associated with each cylinder assembly of the engine such that ignition of the fuel and air mixture occurs within each cylinder assembly at a time prior to each piston of each cylinder assembly reaching a top dead center position.

IPC Classes  ?

• F02D 41/34 - Controlling fuel injection of the low pressure type with means for controlling injection timing or duration
• F02P 7/067 - Electromagnetic pick-up devices

Abstract

A piston aircraft engine assembly includes a piston aircraft engine, a fuel source, and a control system adapted to deliver fuel from the fuel source to the piston aircraft engine. The control system includes a mass airflow sensing apparatus adapted provide a pressure signal, an electronic engine controller coupled to the mass airflow sensing apparatus, and a set of fuel injectors. The electronic engine controller is adapted to (i) receive the pressure signal from the mass airflow sensing apparatus and (ii) generate a set of fuel injector signals based on the pressure signal received from the mass airflow sensing apparatus. The set of fuel injectors is adapted to meter the fuel in response to the set of fuel injector signals generated by the electronic engine controller.

IPC Classes  ?

• F02D 41/18 - Circuit arrangements for generating control signals by measuring intake air flow
• G01F 1/88 - Indirect mass flowmeters, e.g. measuring volume flow and density, temperature, or pressure with differential-pressure measurement to determine the volume flow

Abstract

A piston aircraft engine assembly includes a piston aircraft engine, a fuel source, and a control system adapted to deliver fuel from the fuel source to the piston aircraft engine. The control system includes a mass airflow sensing apparatus adapted provide a pressure signal, an electronic engine controller coupled to the mass airflow sensing apparatus, and a set of fuel injectors. The electronic engine controller is adapted to (i) receive the pressure signal from the mass airflow sensing apparatus and (ii) generate a set of fuel injector signals based on the pressure signal received from the mass airflow sensing apparatus. The set of fuel injectors is adapted to meter the fuel in response to the set of fuel injector signals generated by the electronic engine controller.

IPC Classes  ?

• F02M 7/24 - Controlling flow of aerating air
• F02M 51/00 - Fuel-injection apparatus characterised by being operated electrically

Abstract

An aircraft engine includes a cylinder assembly knock detection and control system having a set of knock detection sensors and an engine controller. Each cylinder assembly of the aircraft engine carries a knock detection sensor and each knock detection sensor is electrically coupled to the engine controller. During operation, each knock detection sensor transmits signals to the engine controller where the signals correspond to detected cylinder assembly vibrations. As the engine controller receives input signals from the sensors, the engine controller filters the input signals to distinguish the input signals as being associated with either knocking or as a non-knock event. In the case where the engine controller detects the occurrence of one or more knock events in a particular cylinder assembly, the engine controller automatically reduces the spark timing for that cylinder assembly and/or increases the volume of fuel delivered to that cylinder assembly.

IPC Classes  ?

• F02D 35/02 - Non-electrical control of engines, dependent on conditions exterior or interior to engines, not otherwise provided for on interior conditions
• F02P 5/152 - Digital data processing dependent on pinking
• F02D 41/00 - Electrical control of supply of combustible mixture or its constituents
• G01L 23/22 - Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquidIndicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid for detecting or indicating knocks in internal-combustion enginesUnits comprising pressure-sensitive members combined with ignitors for firing internal-combustion engines

Abstract

An aircraft engine power distribution system (28) for an aircraft engine controller (26), such as a FADEC, is provided where the power source (22) is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator (26) operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor (24) that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.

IPC Classes  ?

• B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
• H02J 9/00 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting

Abstract

An aircraft engine power distribution system for an aircraft engine controller, such as a FADEC, is provided where the power source is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.

IPC Classes  ?

• F02D 29/06 - Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto peculiar to engines driving electric generators
• H02P 9/00 - Arrangements for controlling electric generators for the purpose of obtaining a desired output

Abstract

A fuel injector mounting assembly is configured to limit or constrain movement of a fuel injector relative to a corresponding cylinder assembly. For example, the fuel injector mounting assembly includes a base that is secured to a cylinder assembly's housing and a fuel conduit. The fuel conduit includes a first fuel conduit portion which operates in conjunction with a cylinder assembly's fuel manifold to capture a fuel injector between the fuel injector mounting assembly and the cylinder assembly's fuel manifold. The fuel conduit also includes a second fuel conduit portion which is secured to a compliant fuel line. With such a configuration of the fuel injector mounting assembly, both ends of the fuel injector are secured to the cylinder assembly to minimize any relative motion in the fuel injector's seals relative to either the cylinder assembly's fuel manifold or to the compliant fuel line.

IPC Classes  ?

• F02M 61/14 - Arrangements of injectors with respect to enginesMounting of injectors
• F02M 63/02 - Fuel-injection apparatus having several injectors fed by a common pumping element, or having several pumping elements feeding a common injectorFuel-injection apparatus having provisions for cutting-out pumps, pumping elements, or injectorsFuel-injection apparatus having provisions for variably interconnecting pumping elements and injectors alternatively
• F02M 55/00 - Fuel-injection apparatus characterised by their fuel conduits or their venting means
• B23P 11/00 - Connecting or disconnecting metal parts or objects by metal-working techniques, not otherwise provided for

Abstract

An engine (50) includes a fuel delivery system (56) having a fuel rail (80) and fuel delivery devices (59), such as fuel injectors, that deliver fuel to corresponding cylinder assemblies (60). The use of the fuel rail and fuel injectors allows unused fuel to be purged from the engine at the end of the engine's operating cycle, thereby minimizing the creation of fuel vapor within the engine. The fuel delivery system also includes fuel rail coupling members (84) that are constructed and arranged to secure each cylinder assembly to the fuel rail and to absorb load generated by the corresponding cylinder assembly on the fuel rail during operation. The fuel rail coupling members allow motion of the cylinder assemblies relative to the fuel rail during operation and minimize the application of potentially damaging forces on the fuel rail.

IPC Classes  ?

• F02M 63/02 - Fuel-injection apparatus having several injectors fed by a common pumping element, or having several pumping elements feeding a common injectorFuel-injection apparatus having provisions for cutting-out pumps, pumping elements, or injectorsFuel-injection apparatus having provisions for variably interconnecting pumping elements and injectors alternatively
• F02M 55/02 - Conduits between injection pumps and injectors
• F02M 61/14 - Arrangements of injectors with respect to enginesMounting of injectors

Abstract

An engine includes a fuel delivery system having a fuel rail and fuel delivery devices, such as fuel injectors, that deliver fuel to corresponding cylinder assemblies. The use of the fuel rail and fuel injectors allows unused fuel to be purged from the engine at the end of the engine's operating cycle, thereby minimizing the creation of fuel vapor within the engine. The fuel delivery system also includes fuel rail coupling members that are constructed and arranged to secure each cylinder assembly to the fuel rail and to absorb load generated by the corresponding cylinder assembly on the fuel rail during operation. The fuel rail coupling members allow motion of the cylinder assemblies relative to the fuel rail during operation and minimize the application of potentially damaging forces on the fuel rail.

IPC Classes  ?

• F02M 69/46 - Details, component parts or accessories not provided for in, or of interest apart from, the apparatus covered by groups

Abstract

An engine test system includes a base constructed and arranged to reside at a fixed location. The system further includes an engine support member constructed and arranged to concurrently support an engine and move relative to the base. The system further includes a linear transducer having (i) a first portion supported by the base, (ii) a second portion supported by the engine support member, and (iii) a circuit adjacent the first and second portions. The circuit is constructed and arranged to provide a linear transducer signal identifying an amount of linear compression and/or tension between the engine support member and the base along a predefined direction. When the linear transducer resides at a break in station, such an embodiment provides a simple, low cost mechanism which is capable of providing a horsepower measurement for every engine passing through the break in station.

IPC Classes  ?

• G01L 3/14 - Rotary-transmission dynamometers wherein the torque-transmitting element is other than a torsionally-flexible shaft
• G01L 3/16 - Rotary-absorption dynamometers, e.g. of brake type

Abstract

An engine includes a fuel rail (79) and fuel delivery devices (59), such as fuel injectors, that deliver fuel to corresponding cylinder assemblies (60). The use of the fuel rail and fuel, injectors allows unused fuel to be purged from the engine at the end of the engine's operating cycle, thereby minimizing the creation of fuel vapor within the engine. The fuel rail is assembled from modular fluid conduit adaptors (80) and fluid conduits (82). With such modularity, a custom fuel rail can be assembled for any size engine. The use of the fluid conduit adaptors and fluid conduits allows motion of the cylinder assemblies relative to the fuel rail during operation to minimize the application of potentially damaging forces on the fuel rail.

IPC Classes  ?

• F02M 55/02 - Conduits between injection pumps and injectors
• F02M 69/46 - Details, component parts or accessories not provided for in, or of interest apart from, the apparatus covered by groups

Abstract

A fuel injector mounting assembly (100) is configured to limit or constrain movement of a fuel injector (102) relative to a corresponding cylinder assembly (60). For example, the fuel, injector mounting -assembly includes a base (110) that is secured to a cylinder assembly's housing and a fuel conduit (112). The-fuel conduit includes a first fuel conduit portion (116) which operates in conjunction with a cylinder assembly' s fuel manifold to capture a fuel injector between the fuel injector mounting assembly and the cylinder assembly's fuel manifold. The fuel conduit also includes a second fuel conduit portion (130) which is secured to a compliant fuel line (82). With such a configuration of the fuel injector mounting assembly, both ends of the fuel injector are secured to the cylinder assembly to minimize any relative motion in the fuel injector's seals relative to either the cylinder assembly's fuel manifold or to the compliant fuel line.

IPC Classes  ?

• F02M 61/14 - Arrangements of injectors with respect to enginesMounting of injectors
• F02M 69/46 - Details, component parts or accessories not provided for in, or of interest apart from, the apparatus covered by groups

Abstract

A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size

IPC Classes  ?

• F04C 2/10 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of internal-axis type with the outer member having more teeth or tooth-equivalents, e.g. rollers, than the inner member
• F02M 37/04 - Feeding by means of driven pumps
• F04C 14/26 - Control of, monitoring of, or safety arrangements for, machines, pumps or pumping installations characterised by using valves controlling pressure or flow rate, e.g. discharge valves using bypass channels

Abstract

An engine includes a fuel rail and fuel delivery devices, such as fuel injectors, that deliver fuel to corresponding cylinder assemblies. The use of the fuel rail and fuel injectors allows unused fuel to be purged from the engine at the end of the engine's operating cycle, thereby minimizing the creation of fuel vapor within the engine. The fuel rail is assembled from modular fluid conduit adaptors and fluid conduits. With such modularity, a custom fuel rail can be assembled for any size engine. The use of the fluid conduit adaptors and fluid conduits allows motion of the cylinder assemblies relative to the fuel rail during operation to minimize the application of potentially damaging forces on the fuel rail.

IPC Classes  ?

• F02M 55/02 - Conduits between injection pumps and injectors
• F02M 69/46 - Details, component parts or accessories not provided for in, or of interest apart from, the apparatus covered by groups

Abstract

In one embodiment, a sensing apparatus senses rotation of an engine component (e.g., a crank shaft) relative to an engine body. The sensing apparatus includes a sensor, and a bracket configured to position the sensor in a fixed location relative to the engine body. The starter ring has (i) a support portion configured to rotate in tandem with the engine component, (ii) a starter interface mounted to the support portion, the starter interface being configured to receive drive from a starter motor during operation of the starter motor, and (iii) a trigger portion mounted to the support portion. The trigger portion is configured to provide a series of indicators during rotation of the engine component. The series of indicators (e.g., a series of magnetic field perturbations during rotation of the engine component) is readable by the sensor thus enabling identification of component positioning and speed.

IPC Classes  ?

• G01M 15/00 - Testing of engines

Abstract

A tappet for an internal combustion engine is formed from a high-carbon, bearing grade steel. The high-carbon, bearing grade steel has a relatively high surface fatigue strength that provides the tappet with the ability to absorb a relatively large contact stresses during operation, thereby minimizing the formation of cracks within the tappet. Additionally, the high-carbon steel tappet can be heat treated to provide a substantially uniform hardness, between about 58 Rockwell Hardness C (HRC) and 62 HRC, and a substantially consistent microstructure throughout the tappet, thereby minimizing wear of the tappet during use.

IPC Classes  ?

• F01L 1/14 - TappetsPush-rods

Abstract

In one embodiment, a sensing apparatus senses rotation of an engine component (e.g., a crank shaft) relative to an engine body. The sensing apparatus includes a sensor, and a bracket configured to position the sensor in a fixed location relative to the engine body. The starter ring has (i) a support portion configured to rotate in tandem with the engine component, (ii) a starter interface mounted to the support portion, the starter interface being configured to receive drive from a starter motor during operation of the starter motor, and (iii) a trigger portion mounted to the support portion. The trigger portion is configured to provide a series of indicators during rotation of the engine component. The series of indicators (e.g., a series of magnetic field perturbations during rotation of the engine component) is readable by the sensor thus enabling identification of component positioning and speed.

IPC Classes  ?

• F02N 15/00 - Other power-operated starting apparatusComponent parts, details, or accessories, not provided for in, or of interest apart from, groups

Abstract

A tappet for an internal combustion engine is formed from a high-carbon, bearing grade steel. The high-carbon, bearing grade steel has a relatively high surface fatigue strength that provides the tappet with the ability to absorb a relatively large contact stresses during operation, thereby minimizing the formation of cracks within the tappet. Additionally, the high-carbon steel tappet can be heat treated to provide a substantially uniform hardness, between about 58 Rockwell Hardness C (HRC) and 62 HRC, and a substantially consistent microstructure throughout the tappet, thereby minimizing wear of the tappet during use.

IPC Classes  ?

• F01L 1/14 - TappetsPush-rods