The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism (80) in a friction fit, and a plurality of ring segments (20.sub.i, 20.sub.i+1), wherein a free axial path length (a.sub.f) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a.sub.1) of a rotation locking member (10) of the outer sealing ring (a.sub.f≧a.sub.1), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a.sub.2) of a radial mounting rail (23) of the outer sealing ring (a.sub.f≧a.sub.2), and/or an axial offset (a.sub.3, a.sub.4) of a sealing fin (31, 41); and/or a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit.

A method and apparatus for holding a panel. A rigid frame is secured on an aircraft on a rework area on the aircraft. A carrier is attached to the rigid frame. The panel is held on the carrier and the carrier moves the panel about a plurality of axes. The panel moves with the carrier such that the panel has a desired position relative to a rework opening in the rework area. The panel is attached to the aircraft while the panel is held in the desired position relative to the rework opening.

An engine system may include a fuel and air supply circuit and an exhaust circuit, a temperature sensor mounted on an exterior of the engine and an oxygen sensor located in the exhaust circuit. The fuel and air supply circuit may include a throttle body mounted on the engine and having a throttle valve to control the flow rate of air delivered to the engine, a fuel injector carried by the throttle body to deliver fuel to the engine and a fuel rail carried by at least one of the throttle body and the fuel injector and having an input to receive a supply of fuel and an outlet through which fuel is routed to the fuel injector. An engine control unit may be communicated with these components to control the fuel and air mixture provided to the engine as a function of the temperature and oxygen sensor outputs.

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 includes a housing and an outer sealing ring. In an assembled state of the housing and the outer sealing ring, a first planar structure of the outer sealing ring is axially moveable with respect to a second planar structure of the housing against a direction of flow through the gas turbine.

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 with a flared end, sealant and instructions for performing the method. 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.

The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism (80) in a friction fit, and a plurality of ring segments (20.sub.i, 20.sub.1+1), wherein .[.a free axial path length (a.sub.f) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a.sub.1) of a rotation locking member (10) of the outer sealing ring (a.sub.fa.sub.1), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a.sub.2) of a radial mounting rail (23) of the outer sealing ring (a.sub.fa.sub.2), and/or an axial offset (a.sub.3, a.sub.4) of a sealing fin (31, 41); and/or.]. a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit .Iadd.and pi is at least as large as a difference between a maximum outer diameter of the outer sealing ring and a minimum inner diameter of the flow channel inlet of the housing.Iaddend..

A gas turbine engine includes a fan that includes a plurality of fan blades rotatable about an axis. An on-wing portion includes a compressor section and a combustor that is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A core flow path is arranged within a core nacelle. The fan is arranged upstream from the core flow path. A fan drive gear system module is coupled to the turbine section for rotating the fan about the axis. A connector assembly including first and second members respectively is secured to the on-wing portion and the fan drive gear system module. The first and second members are removably secured to one another by radially extending fasteners. The first members are connected to an on-wing portion of the gas turbine engine and the second members are connected to the fan drive gear system module. The fasteners are accessible through the bypass flow path.

An arrangement for supplying fuel from a fuel pressure source located on an outside of an engine enclosure to a fuel injector located on an inside of the engine enclosure includes a fuel pipe for transporting fuel from the fuel pressure source to the fuel injector via an opening in the engine enclosure, and a seal for sealing the fuel pipe at the opening. The seal includes a first part configured for a sealing contact around the fuel pipe and a second part configured for a sealing contact around a sleeve extending around the opening. An internal combustion engine provided with such an arrangement and a method for providing an internal combustion engine with such an arrangement are also provided.

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.