公开(公告)号：US20180258856A1

公开(公告)日：2018-09-13

申请号：US15452632

申请日：2017-03-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Steven D. Sandahl

IPC: F02C7/045 ,  F01D25/06

CPC classification number: F02C7/045 ,  B64D2033/0206 ,  F01D5/26 ,  F01D25/06 ,  F02K3/06 ,  F05D2260/96 ,  F05D2300/516 ,  Y02T50/672 ,  Y02T50/673

Abstract: Disclosed is a gas turbine engine including a fan, a nacelle including a flutter damper forward of the fan, the flutter damper including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber in fluid communication with the acoustic liner, and the chamber configured for peak acoustical energy absorption at a frequency range associated with fan flutter modes, and the engine includes (i) the nacelle and a core cowl forming a convergent-divergent fan exit nozzle; (ii) a variable area fan nozzle capable of being in an opened and closed, the opened position having a larger fan exit area than the closed position; and/or (iii) the fan being shrouded.

公开(公告)号：US10060357B2

公开(公告)日：2018-08-28

申请号：US15292472

申请日：2016-10-13

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/107 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F01D11/12

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D11/122 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/20 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F04D19/02 ,  F05B2250/283 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

公开(公告)号：US20180230946A1

公开(公告)日：2018-08-16

申请号：US15343470

申请日：2016-11-04

Applicant: United Technologies Corporation

Inventor： John P. Virtue, JR. ,  Rishon Saftler ,  Frederick M. Schwarz

IPC: F02K3/068 ,  F04D29/64 ,  F01D11/18 ,  F02K3/02 ,  F02K3/06 ,  F02K3/075 ,  B64D27/00 ,  F02K3/11 ,  F01D25/16

CPC classification number: F02K3/068 ,  B64D2027/005 ,  F01D11/18 ,  F01D19/00 ,  F01D25/16 ,  F01D25/164 ,  F01D25/36 ,  F02C7/26 ,  F02C7/32 ,  F02C9/42 ,  F02K3/025 ,  F02K3/06 ,  F02K3/075 ,  F02K3/11 ,  F04D29/642 ,  F05D2220/3219 ,  F05D2220/36 ,  F05D2260/80 ,  F05D2260/84 ,  F05D2260/85 ,  Y02T50/671

Abstract: An aspect includes a system including a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%. The cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions.

公开(公告)号：US20180209339A1

公开(公告)日：2018-07-26

申请号：US15925811

申请日：2018-03-20

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C6/08 ,  F02C7/32 ,  B64D13/04 ,  F02C9/18 ,  B64D13/06

CPC classification number: F02C6/08 ,  B64D13/04 ,  B64D2013/0644 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/323

Abstract: An environmental control system includes a low pressure tap at a location on a first compressor section of a main compressor section. The low pressure tap communicates airflow to a first passage leading to a downstream outlet. A compressor is driven by an electric motor. A combined outlet intermixes airflow from the first passage and from the compressor driven by the electric motor and passes the airflow downstream to be delivered to an aircraft use.

公开(公告)号：US10030586B2

公开(公告)日：2018-07-24

申请号：US14789300

申请日：2015-07-01

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02C7/36 ,  F02K3/072 ,  F02K3/04 ,  F02K3/06 ,  F02C3/107 ,  F02C3/36 ,  F01D9/06 ,  F02C7/06 ,  F01D5/06 ,  F01D9/02 ,  F02C3/04 ,  F02C9/18 ,  F02K1/78 ,  F04D27/00 ,  F04D29/32

Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

公开(公告)号：US09976437B2

公开(公告)日：2018-05-22

申请号：US14824351

申请日：2015-08-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

IPC: F16H57/08 ,  F01D15/12 ,  F01D25/18 ,  F01D25/16 ,  F01D1/02 ,  F01D5/02 ,  F02C7/32 ,  F16H57/04

CPC classification number: F01D15/12 ,  F01D1/02 ,  F01D5/02 ,  F01D5/027 ,  F01D25/16 ,  F01D25/18 ,  F02C7/32 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/40311 ,  F16H57/0423 ,  F16H57/0479 ,  F16H57/0486 ,  F16H2057/085

Abstract: A turbine engine has a fan shaft. At least one tapered bearing is mounted on the fan shaft. The fan shaft includes at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear. A ring gear surrounds and meshes with the intermediate gears. Each of the intermediate gears are supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train. The turbine section has a fan drive turbine that includes a pressure ratio that is greater than about 5. The fan includes a pressure ratio that is less than about 1.45, and the fan has a bypass ratio of greater than about ten (10).

公开(公告)号：US20180135454A1

公开(公告)日：2018-05-17

申请号：US15856396

申请日：2017-12-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F01D15/12 ,  F04D25/04 ,  F02K3/06 ,  F04D29/053 ,  F01D5/06 ,  F04D19/00

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear lateral stiffness and a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral stiffness and the ring gear transverse stiffness is less than 12% of a respective one of the gear mesh lateral stiffness the ring gear transverse stiffness.

公开(公告)号：US20180128187A1

公开(公告)日：2018-05-10

申请号：US15346187

申请日：2016-11-08

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Nathan Snape

IPC: F02C9/28 ,  F02C3/04 ,  F01D17/08 ,  F02C7/18 ,  F01D21/12

CPC classification number: F02C9/28 ,  F01D17/085 ,  F01D21/12 ,  F02C3/04 ,  F02C7/185 ,  G01K13/02 ,  G01K2013/024

Abstract: A temperature detection device located downstream a cooling network coupled to a gas turbine engine and located upstream of at least one of a compressor rotor of a compressor section of the gas turbine engine and a turbine rotor of a turbine section of the gas turbine engine, is provided. The temperature detection device includes at least one thermocouple configured to detect an operational temperature of the cooling network. The temperature detection device communicates the operational temperature to a control system.

公开(公告)号：US20180119564A1

公开(公告)日：2018-05-03

申请号：US15856441

申请日：2017-12-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F01D15/12 ,  F02K3/06 ,  F04D29/053 ,  F04D25/04 ,  F04D19/00 ,  F01D5/06

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. A gear system input connected to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness At least one of the gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.

公开(公告)号：US20180073392A1

公开(公告)日：2018-03-15

申请号：US15801611

申请日：2017-11-02

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  William K. Ackermann ,  Daniel Bernard Kupratis ,  Michael E. McCune

IPC: F01D25/16 ,  F02C3/107 ,  F04D29/056 ,  F02C7/06 ,  F02C7/20 ,  F04D29/66 ,  F01D5/06 ,  F01D9/04

CPC classification number: F01D25/164 ,  F01D5/06 ,  F01D9/041 ,  F01D15/12 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/028 ,  F04D25/045 ,  F04D29/056 ,  F04D29/325 ,  F04D29/668 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan and a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.