Two-turbine Geared Engine with Low Pressure Environmental Control System for Aircraft

Content Provider	The Lens
Abstract	A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. A pylon supports the gas turbine engine. An environmental control system includes a higher pressure tap at a higher pressure location in the main compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. The pylon includes a lowermost surface and the higher pressure tap does not extend above a plane including the lowermost surface. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. An environmental control system is also disclosed.
Related Links	https://www.lens.org/lens/patent/009-309-272-934-636/frontpage
Language	English
Publisher Date	2019-01-03
Access Restriction	Open
Content Type	Text
Resource Type	Patent
Jurisdiction	United States of America
Date Applied	2014-06-27
Applicant	Schwarz Frederick M Suciu Gabriel L
Application No.	201415932447
Claim	A gas turbine engine assembly comprising: a fan section delivering air into a main compressor section, said main compressor section compressing air and delivering air into a combustion section, products of combustion passing from said combustion section over a turbine section to drive said fan section and main compressor sections, wherein a gearbox is driven by said turbine section to drive said fan section; a pylon supporting the gas turbine engine; an environmental control system including a higher pressure tap at a higher pressure location in said main compressor section, and a lower pressure tap at a lower pressure location, said lower pressure location being at a lower pressure than said higher pressure location; said lower pressure tap communicating to a first passage leading to a downstream outlet and a compressor section of a turbocompressor; said higher pressure tap leading into a turbine section of said turbocompressor such that air in said higher pressure tap drives said turbine section to in turn drive said compressor section of said turbocompressor, wherein the pylon includes a lowermost surface and the higher pressure tap does not extend above a plane including the lowermost surface; and a combined outlet of said compressor section and said turbine section of said turbocompressor intermixing and passing downstream to be delivered to an aircraft use. The gas turbine engine assembly as recited in claim 1 , wherein the fan drive gearbox provides a gear reduction of at least about 2.0. The gas turbine engine assembly as recited in claim 1 , wherein the turbine section includes a fan drive turbine that drives the gearbox and one of the main compressor sections. The gas turbine engine assembly as recited in claim 1 , wherein the main compressor section includes a first compressor section and a second compressor section and the first compressor section includes at least four (4) stages and no more than seven (7) stages. The gas turbine assembly engine as recited in claim 4 , wherein bleed air is taken from at least a fourth stage of the first compressor section. The gas turbine engine assembly as recited in claim 1 , wherein the turbine section includes a first turbine section driving a high pressure compressor, an intermediate turbine section driving a low pressure compressor and a third turbine section driving the fan section. The gas turbine engine assembly as recited in claim 1 , wherein the main compressor section includes a first compressor section and a second compressor section and the first compressor section includes at least three (3) stages and no more than eight (8) stages. The gas turbine engine assembly as recited in claim 7 , wherein bleed air is taken from at least a third stage of the first compressor section. The gas turbine engine assembly as recited in claim 1 , including a control valve in fluid communication with an inlet to the compressor of the turbocompressor. The gas turbine engine assembly as recited in claim 1 , including a valve disposed between low pressure tap and the compressor section of the turbocompressor. The gas turbine engine assembly as recited in claim 1 , including a sensor generating data indicative of a speed of the turbine of the turbocompressor. The gas turbine engine assembly as recited in claim 11 , including a brake for controlling rotation of the turbine of the turbocompressor responsive to detection of an overspeed condition An environmental control system for an aircraft comprising: a higher pressure tap to be associated with a higher pressure location in a main compressor section associated with an engine of the aircraft, and a lower pressure tap to be associated with a lower pressure location in said main compressor section, said lower pressure location being at a lower pressure than said higher pressure location; said lower pressure tap communicating to a first passage leading to a downstream outlet, and a compressor section of a turbocompressor; said higher pressure tap leading into a turbine section of said turbocompressor such that air in said higher pressure tap drives said turbine section to in turn drive said compressor section of said turbocompressor, wherein said higher pressure tap is disposed below a plane including a lowermost surface of a pylon supporting the main compressor section associated with the engine of the aircraft; and a combined outlet of said compressor section and said turbine section of said turbocompressor intermixing and passing downstream to be delivered to an aircraft use. The environmental control system as recited in claim 13 , wherein a check valve is disposed within said first passage associated with said lower pressure tap. The environmental control system as recited in claim 13 , wherein a control valve is positioned on said higher pressure tap, and may be closed to drive air through said first passage associated with said lower pressure tap, or to have air pass through said compressor section of said turbocompressor when said control valve is opened. The environmental control system as recited in claim 13 , wherein a redundant valve is provided to be closed if said control valve associated with said higher pressure tap fails. The environmental control system as recited in claim 16 , wherein said redundant valve is positioned to be downstream of a location at which said first passage and said combined outlet intermix into a common conduit. The environmental control system as recited in claim 13 , including a control valve disposed between the low pressure tap and the compressor section of the turbocompressor. The environmental control system as recited in claim 13 , including a sensor generating data indicative of a speed of the turbine section of the turbocompressor. The environmental control system as recited in claim 19 , including a brake for controlling rotation of the turbine of the turbocompressor responsive to detection of an overspeed condition.
CPC Classification	GAS-TURBINE PLANTS;AIR INTAKES FOR JET-PROPULSION PLANTS;CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT;FLIGHT SUITS;PARACHUTES;ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT INDEXING SCHEME RELATING TO WIND; SPRING; WEIGHT; INERTIA OR LIKE MOTORS; TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B; F03D AND F03G INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES; GAS-TURBINES OR JET-PROPULSION PLANTS Climate Change Mitigation Technologies Related To Transportation Non-Positive Displacement Machines Or Engines; E.G. Steam Turbines NON-POSITIVE-DISPLACEMENT PUMPS
Extended Family	149-723-732-688-844 127-245-278-054-363 009-309-272-934-636 199-450-343-432-944 014-063-833-538-240 012-181-167-382-460 111-995-075-955-139 189-648-038-722-292 077-813-170-740-362 134-844-078-458-185 053-922-630-467-697 028-729-194-285-588 016-696-144-963-877 009-019-180-836-371 136-860-822-267-428 006-520-129-686-099 102-057-306-412-549 008-932-482-598-069 173-430-639-192-124 098-930-952-347-850 193-536-094-074-822 103-994-796-229-773 193-662-436-073-967 119-088-098-520-471
Patent ID	20190003382
Inventor/Author	Schwarz Frederick M Suciu Gabriel L
IPC	F02C6/08 B64D13/06 F01D21/02 F04D27/00
Status	Active
Owner	Rtx Corporation
Simple Family	009-309-272-934-636 014-063-833-538-240
CPC (with Group)	F02C6/08 B64D13/06 B64D2013/0618 B64D2013/0648 F05B2270/1011 F05D2260/40311 F05D2260/90 F05D2270/021 F05D2270/304 Y02T50/50 F01D21/02 F02C6/04 F02C6/06 F04D27/008 F05D2220/323 F05D2260/4031
Issuing Authority	United States Patent and Trademark Office (USPTO)
Kind	Patent Application Publication