Engine

US D885 438S1

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Claims

The ornamental design for an engine, as shown and described.

Description

FIG. 1 is a front perspective view of an engine showing the new design.

FIG. 2 is a rear perspective view of an engine showing the new design.

FIG. 3 is a front view of an engine showing the new design.

FIG. 4 is a rear view of an engine showing the new design.

FIG. 5 is a first side view of an engine showing the new design.

FIG. 6 is a top view of an engine showing the new design.

FIG. 7 is a second side view of an engine showing the new design; and,

FIG. 8 is a bottom view of an engine showing the new design.

Citations

US 2005 60,982 A1 - Method and system for reduction of jet engine noise
In an aspect, a method is provided for attenuating jet engine noise. Air velocity, adjacent to an inlet fan duct outer wall, is increased to...

US 2010 205,933 A1 - Regeneratively cooled porous media jacket
The fluid and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is...

US 2020 52,570 A1 - TURBOFAN JET ENGINE, POWERED BY AN ELECTRIC MOTOR WITH POWER FROM A HIGH EFFICIENCY ELECTRIC GENERATOR
A power system for an aircraft engine provides rotational drive to propeller driven and turbofan jet engine powered aircraft by use of a propeller or...

US 2007 245,741 A1 - Methods and system for reducing pressure losses in gas turbine engines
A method of assembling a combustor assembly is provided, wherein the method includes providing a combustor liner having a centerline axis and defining a combustion...

US 2018 280,851 A1 - JET ENGINE WITH A CHAMBER
A jet engine with a chamber which is delimited by a housing and inside of which a rotatable appliance that can be impinged by hydraulic...

US 2010 8,772 A1 - NACELLE FOR THE JET ENGINE OF AN AIRCRAFT
The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure (6) that defines, together with...

US 2016 40,552 A1 - MODULATED TURBINE COOLING SYSTEM
A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating...

US 2015 377,033 A1 - COOLING HOLE FOR A GAS TURBINE ENGINE COMPONENT
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal...

US 2014 161,618 A1 - Metal Joining And Strengthening Methods Utilizing Microstructural Enhancement
A method for joining first and second metal portions includes welding together the portions such that a weld nugget joins them, compressively stressing the weld...

US 2018 73,391 A1 - TURBINE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE BLADE TRACK AND ACTIVELY COOLED METALLIC CARRIER
A turbine assembly for a gas turbine engine is disclosed herein. The turbine assembly includes a source of cooling air and a turbine shroud configured...

US 2016 186,689 A1 - Thermoformed Cascades for Jet Engine Thrust Reversers
A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and...

US 2017 159,490 A1 - GAS TURBINE ENGINE FLUID COOLING SYSTEMS AND METHODS OF ASSEMBLING THE SAME
A fluid cooling system for use in a gas turbine engine including a fan casing circumscribing a core gas turbine engine includes a heat source...

US 2016 169,516 A1 - GAS TURBINE ENGINE COMBUSTOR BULKHEAD ASSEMBLY
A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the...

US 2018 38,278 A1 - CONSTANT-VOLUME COMBUSTION SYSTEM FOR A TURBINE ENGINE OF AN AIRCRAFT ENGINE
A constant-volume combustion system is for a turbine engine. The system includes a plurality of combustion chambers regularly distributed around a longitudinal axis; a toroidal...

US 2014 352,797 A1 - AIRCRAFT JET ENGINE
In various embodiments, a jet engine, as described herein, may include a fan case, a fan cowl, and an air inlet. Further, in various embodiments,...

US 2013 14,515 A1 - LINK BETWEEN THE EXHAUST CASING AND A STRUCTURAL RING OF THE FAN DUCT OF A JET ENGINE
An assembly including an outer ring of an exhaust casing, a structural ring of an external duct of a fan channel and of a two-flow...

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