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US 8,938,943 B2Granted
Gas turbine engine with bypass mixer
AssigneeRolls-Royce North American Technoloies, Inc.
InventorsKaare Erickson, Randall E. Yount
Life of this patent
Estimating the term…
Abstract
One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
Claims17
A gas turbine engine, comprising:
- a fan system operative to generate a bypass flow;
- a bypass duct in fluid communication with the fan system and operative to transmit the bypass flow from the fan system;
- a compressor system in fluid communication with the fan system;
- a combustion system in fluid communication with the compressor system;
- a turbine system in fluid communication with the combustion system and operative to discharge an engine core flow;
- an engine nozzle in fluid communication with the fan system and the turbine system, wherein the engine nozzle is operative to receive the bypass flow and the core flow and to discharge both as an engine exhaust flow;
- and
- a variable area bypass mixer configured to vary a ratio of the bypass flow to the core flow directed into the engine nozzle to form the engine exhaust flow, wherein the variable area bypass mixer includes an axially translatable sled structured to form a bypass exit flow area for the bypass flow as it merges with the engine core flow, the bypass exit flow area defined between a downstream end of the axially translatable sled and a sidewall;
- and wherein the variable area bypass mixer is configured to axially translate the sled between a first position yielding a maximum bypass exit flow area of the bypass duct that directly provides bypass flow to the core flow and is exposed to the engine nozzle and a second position yielding a minimum bypass exit flow area of the bypass duct that directly provides bypass flow to the core flow and is exposed to the engine nozzle, the first position being upstream of the second position,
- wherein the turbine system includes a discharge portion having an inner core flowpath wall;
- and wherein the sled forms at least a portion of an outer core flowpath wall.
8 more elements
A gas turbine engine, comprising:
- a fan system operative to generate a bypass flow;
- a bypass duct in fluid communication with the fan system and operative to transmit the bypass flow from the fan system, wherein the bypass duct includes a bypass duct discharge portion operative to discharge the bypass flow;
- a compressor system in fluid communication with the fan system;
- a combustion system in fluid communication with the compressor system;
- a turbine system in fluid communication with the combustion system and operative to discharge an engine core flow, wherein the turbine system includes a turbine system discharge portion operative to discharge the core flow;
- a discharge duct in fluid communication with the turbine system discharge portion and the bypass duct discharge portion, wherein the discharge duct is configured to receive the bypass flow and the core flow, and to discharge an engine exhaust flow formed of the bypass flow and the core flow;
- and
- a slidably translatable flowpath wall structure configured to translate in an upstream direction to increase an exit flow area of the bypass duct discharge portion exposed to the discharge duct, and to translate in a downstream direction to decrease the flow area, the exit flow area defined between the downstream end of the slidably translatable flowpath wall structure and an adjacent wall,
- wherein the turbine system includes a discharge portion having an inner core flowpath wall;
- and wherein the translatable flowpath wall structure forms at least a portion of an outer core flowpath wall.
7 more elements
Dependencies are inferred from the claim text.