Patent application number | Description | Published |
20100240572 | SPRAY-BASED DEGREASING FLUID - Disclosed is a composition for degreasing surfaces comprising about 75 to about 99.9% by volume parachlorobenzotrifluoride and about 0.1 to about 25% by volume of an organic modifier selected from the group consisting of odorless mineral spirits, an alkane from C1 to C8, acetone, an alcohol from C1 to C8, benzene, xylene, toluene, Stoddard's solvent, t-butyl acetate, a glycol, isoparaffin, and dimethylene carbonate. Additionally, it relates to a degreasing fluid comprising parachlorobenzotrifluoride to be applied using a spray application. | 09-23-2010 |
20100240573 | SPRAY-BASED DEGREASING FLUID - Disclosed is a composition for degreasing surfaces comprising about 97.4 to 100% by volume parachlorobenzotrifluoride and 0 to about 2.6% by volume of a masking agent. Further provided is a method for degreasing surfaces comprising the above composition and providing a spray application means for applying the composition. | 09-23-2010 |
Patent application number | Description | Published |
20090133376 | COMBINED GEARBOX BREATHER AND DRAIN MAST FOR JET AIRCRAFT ENGINE - A combined gearbox breather and drain mast is mounted to a nacelle. The combined gearbox breather and drain mast is made of a composite material and includes a body portion made of a single component with a first passage in fluid communication with a gearbox and a second passage in fluid communication with an engine component. The first passage is separate from the second passage. | 05-28-2009 |
20090301095 | PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL - A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle. | 12-10-2009 |
20100074739 | PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL - A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle. | 03-25-2010 |
20100180571 | MODULATING FLOW THROUGH GAS TURBINE ENGINE COOLING SYSTEM - A gas turbine engine system includes a fan bypass passage in a cooling passage having an inlet that receives a bleed flow from the fan bypass passage and an outlet that discharges the bleed flow into the fan bypass passage. A nozzle having a variable cross-sectional area controls an airflow within the fan bypass passage. The bleed flow outlet is placed such that moving the nozzle to change the variable cross-sectional area controls an amount of the bleed flow through the cooling passage. | 07-22-2010 |
20130219857 | BYPASS DUCT WITH ANGLED DRAG LINKS - A gas turbine engine includes an engine core outer casing and a fan nacelle spaced radially outwardly relative to the engine core outer casing to define a bypass duct. A plurality of drag links is used to pivot blocker doors into a flow blocking position in the bypass duct when a thrust reverser is deployed. The plurality of drag links is located within the bypass duct in an area of non-uniform flow defined by a plurality of local airflow angles. Each drag link is individually configured to align with one of the local flow angles. | 08-29-2013 |
20140053532 | NACELLE SCOOP INLET - A scoop inlet for use in a gas turbine engine nacelle has a scoop inlet, and a tab extending forwardly of the scoop inlet. The scoop communicates with a downstream flowpath. The tab has at least one opening at a location upstream of the scoop inlet. A nacelle and a gas turbine engine are also disclosed. | 02-27-2014 |
20140169935 | LIGHTWEIGHT SHROUDED FAN BLADE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis. Each of the plurality of fan blades includes a mid-span shroud and a speed change device in communication with the fan. | 06-19-2014 |
20140260182 | FREE STREAM INTAKE FOR REVERSE CORE ENGINE - A gas turbine engine has a fairing and an air intake that includes an air inlet embedded within the fairing for supplying free stream atmospheric air to a gas generator. | 09-18-2014 |
20140321970 | PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL - A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section. | 10-30-2014 |