Abstract: A pendent residential fire prevention sprinkler has a frame structure extending from the sprinkler body, and a system for blocking an outlet to prevent fluid from passing through the outlet until occurrence of a predetermined condition and for unblocking the outlet in response to occurrence of the condition. A deflector is supported by the frame structure at a predetermined distance from the outlet, at a position to be impinged upon by the fluid leaving the outlet. The deflector has a central portion and a peripheral portion, and slots formed in the periphery, defining tines therebetween. The slots include a first plurality of slots, each of which extends inward from the deflector periphery with a uniform width, a second plurality of slots, each of which has a first portion and a second portion between the deflector periphery and the slot's closed end, where the first portion has a width that varies at different points, while the second portion has a uniform width.

Abstract: A laminate air seal for a gas turbine engine includes at least one fabric layer made of fiberglass, ceramic fiber, basalt and/or carbon, and a polymeric resin that is stable at an operating temperature of the gas turbine engine. The resin may be preimpregnated into the fabric layers, or introduced into the fabric during assembly and formation of the laminate. The resin may be polyimide, bismaelimide (BMI) or cyanate ester. A particular resin selected may depend, in part, on the operating temperatures in that region of the gas turbine engine. In some embodiments, the laminate seal may include a coating to increase lubricity of the seal. In one embodiment, the laminate air seal is used to seal a gap between a pylon fairing and an exhaust nozzle of the turbine engine.

Abstract: The invention comprises an abradable material containing up to 30 weight percent of fumed silica having a maximum particle from about 5 nanometers to about 20 nanometers and about 1.5 to about 5 weight percent of an abradable organic microballoon filler within an abradable silicone polymer matrix having an elasticity of less than X percent.

Abstract: The invention comprises an abradable material containing up to 30 weight percent of fumed silica having a maximum particle from about 5 nanometers to about 20 nanometers and about 1.5 to about 5 weight percent of an abradable organic microballoon filler within an abradable silicone polymer matrix having an elasticity of less than X percent.

Abstract: A heater assembly for deicing and/or anti-icing a component includes a metallic heating element adjacent to a densely woven fabric layer impregnated with a resin that is capable of withstanding temperatures of up to 550° F. (288° C.).

Abstract: A method and system is described herein for using a polyimide adhesive to bond a first metal layer to a second metal layer used in a gas turbine engine. The polyimide adhesive may be a film or a paste and is able to withstand operating temperatures in excess of 600 degrees Fahrenheit (315 degrees Celsius). In an exemplary embodiment, the second metal layer is an outer face skin of an exhaust nozzle and the first metal layer is a metal doubler configured to cover a damaged portion of the outer face skin. In some embodiments, the first and second metal layers may be formed of titanium.

Abstract: A laminate air seal for a gas turbine engine includes at least one fabric layer made of fiberglass, ceramic fiber, basalt and/or carbon, and a polymeric resin that is stable at an operating temperature of the gas turbine engine. The resin may be preimpregnated into the fabric layers, or introduced into the fabric during assembly and formation of the laminate. The resin may be polyimide, bismaelimide (BMI) or cyanate ester. A particular resin selected may depend, in part, on the operating temperatures in that region of the gas turbine engine. In some embodiments, the laminate seal may include a coating to increase lubricity of the seal. In one embodiment, the laminate air seal is used to seal a gap between a pylon fairing and an exhaust nozzle of the turbine engine.

Abstract: A composite layer for resisting erosion includes a sacrificial layer for exposure to an erosion environment, a body layer, and an erosion resistant layer located between the sacrificial erosion layer and the body layer for protecting the body layer upon erosion of the sacrificial layer.

Abstract: A pendent residential fire prevention sprinkler has a frame structure extending from the sprinkler body, and a system for blocking an outlet to prevent fluid from passing through the outlet until occurrence of a predetermined condition and for unblocking the outlet in response to occurrence of the condition. A deflector is supported by the frame structure at a predetermined distance from the outlet, at a position to be impinged upon by the fluid leaving the outlet. The deflector has a central portion and a peripheral portion, and slots formed in the periphery, defining tines therebetween. The slots include a first plurality of slots, each of which extends inward from the deflector periphery with a uniform width, a second plurality of slots, each of which has a first portion and a second portion between the deflector periphery and the slot's closed end, where the first portion has a width that varies at different points, while the second portion has a uniform width.

Abstract: A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is movable between a plurality of positions to change an effective area associated with a bypass airflow through a fan bypass passage of a gas turbine engine. A protective coating is disposed on the nozzle section and resists change in the effective area of the nozzle section caused by environmental conditions.

Abstract: Compositions and methods for improving the adhesion of a film to a nonwoven, a film to another film, or a nonwoven to another nonwoven are disclosed. Depending on the laminate or multilaminate structure, the improvement can be achieved by using low viscosity, low density ethylene- or propylene-based polymers, which physically anchor to the substrate, such as a porous nonwoven, or by using a similar polymer in a blend with one of the substrate film polymers to improve flow and adhesion.

Abstract: A method and system is described herein for repairing a part used in a gas turbine engine, which has a damaged or worn lubricant layer bonded to a surface of the part. After removing the damaged or worn lubricant layer, a polymeric adhesive may be used to attach a replacement lubricant layer to the metal surface. The polymeric adhesive may be a film or a paste. In some embodiments, the adhesive includes a non-metallic filler. The polymeric adhesive is stable at an operating temperature of the part to which it is attached. In one embodiment, the adhesive is polyimide, which is well-suited for use in a high pressure compressor of the gas turbine engine that operates at high temperatures. In other embodiments, the adhesive is bismaleimide (BMI) or cyanate ester.

Abstract: A heater assembly for deicing and/or anti-icing a component includes a metallic heating element adjacent to a densely woven fabric layer impregnated with a resin that is capable of withstanding temperatures of up to 550° F. (288° C.).

Abstract: A method of surface treating a thin titanium foil having a thickness of less than about 3 mils is used to facilitate adequate bonding of the foil with an adhesive. The method includes cleaning the foil with an acid solution and further cleaning the foil using an ultrasonic water treatment. Additional steps that may optionally be performed in between the acid solution and the ultrasonic water treatment include cleaning the foil with a first alkaline cleaner, followed by etching and desmuting the foil.

Abstract: A stator assembly having an inner shroud assembly formed of an inner shroud and rubstrip is disclosed. Various construction details and features are developed which relate to durability and manufacturing feasibility are developed. In one detailed embodiment, at the rubstrip is bonded to the thermoplastic shroud. The method is applicable to joining an elastomer, such as silicone rubber material, to a thermoplastic substrate.

Abstract: An abradable material for use at moderate temperatures which is particularly suited for use in the compressor sections of gas turbine engines. Abradable seals of the invention comprise an abradable silicone polymer matrix which contains a dispersion of hard abradable organic filler particles.

Abstract: A method for preparing an uncured supported elastomer material includes the steps of: providing a fibrous reinforcement material; providing a layer of uncured elastomer material substantially adjacent to the fibrous reinforcement material; exposing the layer and the fibrous reinforcement to a temperature below a curing temperature and above a flow point of the uncured elastomer material, and a pressure sufficient that the uncured elastomer material flows into the fibrous reinforcement material, so as to provide an uncured supported elastomer material.

Abstract: A method for preparing an uncured supported elastomer material includes the steps of: providing a fibrous reinforcement material; providing a layer of uncured elastomer material substantially adjacent to the fibrous reinforcement material; exposing the layer and the fibrous reinforcement to a temperature below a curing temperature and above a flow point of the uncured elastomer material, and a pressure sufficient that the uncured elastomer material flows into the fibrous reinforcement material, so as to provide an uncured supported elastomer material.

Abstract: A method for preparing an uncured supported elastomer material includes the steps of: providing a fibrous reinforcement material; providing a layer of uncured elastomer material substantially adjacent to the fibrous reinforcement material; exposing the layer and the fibrous reinforcement to a temperature below a curing temperature and above a flow point of the uncured elastomer material, and a pressure sufficient that the uncured elastomer material flows into the fibrous reinforcement material, so as to provide an uncured supported elastomer material.

Abstract: A coating for protection of airfoil surfaces from erosion caused by the impingement of particles in the incoming air stream of a gas turbine engine or on helicopter blades. The coating consists of an epoxy film toughened with hard particles to improve the erosion resistance and softer particles which impede the progression of cracks through the coating. A method for applying the coating is also described.