A double skinned feed or scavenge pipe assembly comprises; an inner pipe (22) and an outer pipe (23) enclosing the inner pipe and defining an annular space (24) between the inner pipe and the outer pipe and a sleeve (28) configured to slip over the outer pipe (23). Complementary threads (29) are provided on an outer wall of the outer pipe (23) and an inner wall of the sleeve (28). A lock, for example in the form of a locking nut (31) is positioned over the outer pipe (23) when the complementary threads (29) of the outer pipe and sleeve are engaged. The configuration of the assembly is such that, in use, the sleeve (28) is slidable between a first position where the inner pipe (22) is accessible and a second position wherein the inner pipe (22) is completely enclosed.

The method allows to detect flameout in a combustor of a turbine system; it includes the steps of: A) measuring angular acceleration of a shaft of the or each turbine of the turbine system, B) calculating a flameout indicator as a function of the angular acceleration, and C) carrying out a comparison between the flameout indicator and at least one threshold.

The method allows to detect flameout in a combustor of a turbine system; it includes the steps of: A) measuring angular acceleration of a shaft of the or each turbine of the turbine system, B) calculating a flameout indicator as a function of the angular acceleration, and C) carrying out a comparison between the flameout indicator and at least one threshold.

There is provided a system and method for detecting excess flow in an engine fluid system, the method comprising sensing a temperature of a fluid flowing in a fluid line of the fluid system, the fluid line located downstream of a fluid flow restrictor configured to receive the fluid from a source upstream thereof and to flow the fluid from the source into the fluid line downstream thereof, comparing the temperature to a temperature threshold, and when the temperature is beyond the temperature threshold, detecting excess flow of the fluid in the fluid line and outputting an excess flow indication accordingly.

A drone includes a frame and a fuselage. The fuselage is coupled to the frame extending away from the frame. The fuselage has a front panel and a bottom panel, and the front panel is positioned at an angle between the bottom surface of the frame and the bottom panel of the fuselage. A first wing is opposite a second wing and are coupled to the frame. The first and second wings extend outwardly from opposite sides of the frame. A first and second mounting member are coupled to the frame and extend outwardly from opposite sides of the frame. A plurality of power generator systems are included and each system is coupled to the first or second mounting member. Each power generator system comprises a power source coupled to a propeller.

An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.

An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.

Various implementations include a ring material used for producing a ring molded article. The ring molded article has two convex portions which respectively protrude on opposite sides of the ring molded article in a direction of a center axis thereof and extend in a direction of a circumference of the ring molded article. A straight line passing through centers of gravity of first and second side regions is inclined by an angle relative to the center axis of the ring material, the first and second side regions are obtained by virtually dividing a one half section of the ring material based on a middle of a maximum height of the ring material in the direction of the center axis of the ring material, and a range of the angle is 7 degrees to 40 degrees.

Various implementations include a ring material used for producing a ring molded article. The ring molded article has two convex portions which respectively protrude on opposite sides of the ring molded article in a direction of a center axis thereof and extend in a direction of a circumference of the ring molded article. A straight line passing through centers of gravity of first and second side regions is inclined by an angle relative to the center axis of the ring material, the first and second side regions are obtained by virtually dividing a one half section of the ring material based on a middle of a maximum height of the ring material in the direction of the center axis of the ring material, and a range of the angle is 7 degrees to 40 degrees.

A fuel conduit for a fuel injector includes a coiled tube with a longitudinal segment arranged along a flow axis and a radial segment. The radial segment extends about the flow axis and is in fluid communication with the longitudinal segment. The wall one or more of the longitudinal and radial segments increases at a thickness transition location offset from a minimum radius of curvature location along the fuel conduit to limit stress within the fuel conduit. Fuel injectors and methods of making fuel injectors are also described.