A system and method for preventing icing in the combustion inlet air path of a gas turbine system. An air intake system of the gas turbine system supplies intake air to a gas turbine engine. The air intake system includes an air filter inlet house to filter the intake air. The air filter inlet house includes at least one filter stage having an array of pulse filters, with each of the pulse filters being hydrophobic. A combustion inlet air path is in fluid communication with the air intake system and the gas turbine engine. The combustion inlet air path receives the filtered air from the air filter inlet house and supplies the filtered air as combustion inlet air to an inlet of the gas turbine engine. A surface of at least one component in the combustion inlet air path includes an anti-icing coating to prevent ice from forming thereon.

A system and method for preventing icing in the combustion inlet air path of a gas turbine system. An air intake system of the gas turbine system supplies intake air to a gas turbine engine. The air intake system includes an air filter inlet house to filter the intake air. The air filter inlet house includes at least one filter stage having an array of pulse filters, with each of the pulse filters being hydrophobic. A combustion inlet air path is in fluid communication with the air intake system and the gas turbine engine. The combustion inlet air path receives the filtered air from the air filter inlet house and supplies the filtered air as combustion inlet air to an inlet of the gas turbine engine. A surface of at least one component in the combustion inlet air path includes an anti-icing coating to prevent ice from forming thereon.

An air supply plenum for an engine, the plenum being disposed upstream of an air intake of the engine, the air intake being provided in a casing of the engine. The air supply plenum includes a first lateral wall and a second lateral wall which together form a conduit in which an air flow flows as the engine functions. Each lateral wall includes a step which forms a transverse recess relative to the direction of the air flow in the air supply plenum, such that an aerodynamic separation occurs in the step when the engine is operating.

The present invention relates to aircraft engine shield placed over the front of the jet turbines and across the wind shield, made up of heavy duty metal or other suitable material to prevent bird strikes, having small air gaps which not only prevents birds from entry but also prevents any other external particle either small or large to enter the wind shield or front turbines which in turn protects the air craft from any problem,

The present invention relates to aircraft engine shield placed over the front of the jet turbines and across the wind shield, made up of heavy duty metal or other suitable material to prevent bird strikes, having small air gaps which not only prevents birds from entry but also prevents any other external particle either small or large to enter the wind shield or front turbines which in turn protects the air craft from any problem,

An anti-bird strike protection net for aircraft jet engine, comprising fixed circular truncated cone, conical protection net body, connection section, and double helix electrical heating wire, wherein the fixed circular truncated cone is secured on the cowl inlet's outside of the aircraft jet engine via which the conical protection net body is connected to the jet engine with the connection section: hinge, catches, and gas springs; The conical protection net body comprises the base of the conical protection net body, the conical support frame, the net which covers the outside of the conical support frame; the double helix electrical heating wire spirally surrounding the surface of the net is used as deicing device.

This invention is an aftermarket add-on device and can be an original integration part as jet engine manufacturing. It's simple and easy to be secured on the cowl inlet without changing the structure of the aircraft jet engine.

An anti-bird strike protection net for aircraft jet engine, comprising fixed circular truncated cone, conical protection net body, connection section, and double helix electrical heating wire, wherein the fixed circular truncated cone is secured on the cowl inlet's outside of the aircraft jet engine via which the conical protection net body is connected to the jet engine with the connection section: hinge, catches, and gas springs; The conical protection net body comprises the base of the conical protection net body, the conical support frame, the net which covers the outside of the conical support frame; the double helix electrical heating wire spirally surrounding the surface of the net is used as deicing device.

This invention is an aftermarket add-on device and can be an original integration part as jet engine manufacturing. It's simple and easy to be secured on the cowl inlet without changing the structure of the aircraft jet engine.

An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

A system includes a foreign object damage (FOD) screen configured to be disposed upstream of an air intake of a gas turbine engine and to keep debris from entering the air intake. The FOD screen is configured to extend across a fluid flow path extending through the air intake into the gas turbine engine. The FOD screen includes a flexible, woven fabric made of a non-metal material and configured to absorb and dissipate energy from the debris, and the flexible, woven fabric includes a tensile strength ranging between 2700 megapascals (mPa) and 3700 mPa.