A case assembly for a gas turbine engine comprising annular case components each having a central axis. Radial struts each have a radial axis and intersect the annular case components. A stress dissipation mass projecting from a continuous surface of at least one of the struts at the intersection with a corresponding annular case component, the stress dissipation mass being on either side of a plane passing through the radial axis of the strut and the central axis of the corresponding annular case component. A method for dissipating thermal and mechanical stresses on a strut in a case assembly for a gas turbine engine is also provided.

A controller for an electronic fuel injection system for an internal combustion engine includes: a plurality of analog-to-digital (A/D) converters; a memory; and a processor communicatively coupled to the A/D converters and the memory. The A/D converters are configured to receive analog electrical signals representing pressures generated by a plurality of pressure sensors disposed at different locations along an air intake path and output corresponding digital signals representing the pressures, one or more of the pressure sensors are disposed in a body of a carburetor rendered permanently inoperable to mix fuel with air flowing in the air intake path, and the processor is configured to receive the digital signals representing the pressures output from the A/D converters and output a mass air flow signal representing a mass air flow rate as to an engine management system to control the electronic fuel injection system based on the received pressure signals.

An internal combustion engine; wherein at least two cylinders continuously communicate via the cylinder head; and wherein the connecting rod in one cylinder is offset from the connecting rod in the second cylinder by a first angle between 8 and 12 degrees as measured from the crankshaft, and a camshaft having a second offset of one-half of the first angle offset.

A method for assembly of a rotor of a gas turbine with a housing and a channel which diverges in a direction of flow includes axially displacing the rotor in the direction of flow. Then, an outer sealing ring whose minimum inside diameter is smaller than the maximum outside diameter of the rotor is axially displaced in the direction of flow.

A mass air flow measurement apparatus for an internal combustion engine includes: a plurality of pressure sensors disposed at different locations along an air intake path of the internal combustion engine, each pressure sensor adapted to sense a pressure of air flowing into the internal combustion engine and output an electrical signal as a pressure signal corresponding to the sensed air pressure; a carburetor having a plurality of booster venturis, the carburetor rendered permanently inoperable to mix fuel with air flowing in the air intake path, a body of the carburetor configured to accept one or more of the plurality of pressure sensors for each of the plurality of booster venturis; and a calculation section that receives the pressure signals and generates a mass air flow signal as an output signal to an engine management system to control an electronic fuel injection system based on the received pressure signals.

A method for disassembly of a rotor, in particular the front rotor of a gas turbine with a housing and a channel which diverges in a direction of flow and in which the rotor is arranged, is disclosed. An embodiment of the method includes axially displacing an outer sealing ring that is radially opposite the rotor, and whose minimum inside diameter is smaller than the maximum outside diameter of the rotor, against the direction of flow. Then, the rotor is axially displaced against the direction of flow, in particular out of the housing. A method for assembly of such a rotor, as well as a tool for the same, is also disclosed.

A repair kit and associated method for repairing an automotive coolant pipe for fluid-conducting within an engine block of an engine includes at least a repair stent, sealant and instructions for performing the method. The repair stent may be a whole tube, or a hollow semi-cylinder defining a gap. The method includes draining coolant from the engine, removing the water pump from the engine without removing the timing chain cover of the engine, inserting the repair stent including a sealant through the coolant passage, wherein the coolant passage extends through the timing chain cover into the engine, re-assembling the water pump to the engine and adding coolant to the engine.

An apparatus and method are presented for repairing damage to the boundary wall between an engine coolant passage and a fuel injector bore in a cylinder head. The method involves removing the fuel injector from the fuel injector bore adjoining the damaged boundary wall and inserting a purpose-built sealant injector tool into the fuel injector bore. The sealant injector tool is dimensionally equivalent to the fuel injector in critical regions so that it conforms to the interior surface of the fuel injector bore. Sealant is injected into the sealant injector tool at high pressure until the sealant flows into the crack between the fuel injector bore and the coolant passage after which the sealant injector tool is removed and the fuel injector reinstalled.

A method of modifying the oil cooling system of a diesel engine includes the steps of removing the original equipment liquid-to-liquid heat exchanger and installing a manifold having a configuration adapted to match the mounting configuration of the oil passages of the original equipment liquid-to-liquid heat exchanger. The manifold has an oil outlet port directed to a remotely mounted oil cooler. The manifold also has a water passage having a configuration that is adapted to match the mounting configuration of the water passages of the original equipment liquid-to-liquid heat exchanger. The water passage causes the entirety of the flow of water to be discharged back to the water cooling system of the engine where it is circulated by the water pump through the water cooling passages in the engine.

A gas turbine engine includes a fan including a plurality of fan blades rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a geared architecture arranged in a housing and driven by the turbine section for rotating the fan about the axis, and a support member that supports the geared architecture within the gas turbine engine. The support member includes an inner portion and an outer portion. One of the inner and outer portions is configured to be coupled to the geared architecture and the other of the inner and outer portions is configured to be coupled to the housing. A plurality of removal features each have at least one engaging surface to facilitate a pulling force on the support member in a direction parallel to the axis. The engaging surfaces on each of the removal features are oriented relative to each other to resist any bending moment on the support member during application of the pulling force. A gear system and method are also disclosed.