公开(公告)号：US20190153891A1

公开(公告)日：2019-05-23

申请号：US16255980

申请日：2019-01-24

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Bruce L. Morin

IPC: F01D25/04 ,  F02K3/06 ,  F04D29/32 ,  F01D15/12 ,  F01D9/06 ,  F01D5/06 ,  F01D17/10 ,  F02C3/107 ,  F01D5/14

Abstract: A turbine section including a high pressure turbine, an intermediate pressure turbine and a fan drive turbine, the fan drive turbine driving a gear reduction to in turn drive a fan, and effecting a reduction in the speed of the fan relative to an input speed from the fan drive turbine and said high pressure turbine driving a high pressure compressor, and the intermediate pressure turbine driving a low pressure compressor, with the intermediate pressure turbine having a number of turbine blades in at least one row, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row, and the rotational speed being such that the following formula holds true for the at least one row of the intermediate pressure turbine: (number of blades×speed)/60≥5500 Hz.

公开(公告)号：US10288011B2

公开(公告)日：2019-05-14

申请号：US15488630

申请日：2017-04-17

Applicant: United Technologies Corporation

Inventor： David P. Houston ,  Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02C7/36 ,  F02K3/06 ,  F02K3/072 ,  F01D25/16 ,  F01D5/02 ,  F02C7/06 ,  F01D5/06 ,  F01D9/02 ,  F02C3/04 ,  F02C3/107 ,  F02C9/18 ,  F02K1/78 ,  F04D27/00 ,  F04D29/32 ,  F01D9/04

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

公开(公告)号：US10287917B2

公开(公告)日：2019-05-14

申请号：US14785872

申请日：2014-04-29

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F01D25/24 ,  F02K3/06 ,  F16H1/28 ,  F02C3/107 ,  F01D5/02 ,  F01D5/12 ,  F01D17/10 ,  F04D29/32

Abstract: A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between about 430 and 645.

公开(公告)号：US10287914B2

公开(公告)日：2019-05-14

申请号：US15478706

申请日：2017-04-04

Applicant: United Technologies Corporation

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

IPC: F01D15/12 ,  F01D25/16 ,  F04D25/04 ,  F04D25/02 ,  F04D27/00 ,  F04D29/32 ,  F04D19/02 ,  F01D5/06 ,  F01D9/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F02C3/04

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, 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. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. 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.

公开(公告)号：US20190128182A1

公开(公告)日：2019-05-02

申请号：US16225623

申请日：2018-12-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C3/107 ,  F02C7/06 ,  F04D29/32 ,  F02C7/36 ,  F01D25/16 ,  F04D29/059 ,  F04D25/02 ,  F02K3/06

CPC classification number: F02C3/107 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F04D25/028 ,  F04D29/059 ,  F04D29/321 ,  F05D2260/40311

Abstract: A turbofan engine comprising a fan shaft configured to rotate about an axis of the engine. A fan drive gear system is configured to drive the fan shaft. A first spool comprises a high pressure turbine and a high pressure compressor. A second spool comprises a lower pressure turbine, a lower pressure compressor, and a shaft coupling the lower pressure turbine to the intermediate pressure compressor. The engine has a plurality of main bearings. The lower pressure compressor has a plurality of disks and a forward hub mounted to a forwardmost disk.

公开(公告)号：US10247004B2

公开(公告)日：2019-04-02

申请号：US15156382

申请日：2016-05-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John W. Golan ,  Frederick M. Schwarz

IPC: F01D5/08 ,  F28D7/00 ,  F28D7/16 ,  F28F1/04 ,  F28F1/10 ,  F28F9/02 ,  F01D25/12 ,  F04D29/32 ,  F28D21/00 ,  F28F13/08

Abstract: A heat exchanger has a first plurality of fluid passages with an inlet manifold communicating into a core portion, and then an outlet manifold. A second plurality of fluid passages has an inlet manifold communicating into a core portion, and then into an outlet manifold and the core portions of both the first and second pluralities of fluid passages having smaller cross-sectional areas than cross-sectional areas of the inlet and outlet manifolds. A gas turbine engine and a method of forming a heat exchanger are also disclosed.

公开(公告)号：US10202185B2

公开(公告)日：2019-02-12

申请号：US14709744

申请日：2015-05-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz

IPC: B64C11/14 ,  F02K3/06 ,  F02C3/107 ,  F02C7/04 ,  F02C7/36

Abstract: A fan section comprises a fan rotor having a plurality of blades and a spinner positioned forwardly of the fan rotor. The fan rotor is driven through a gear reduction. The spinner includes a spinner body having an outer surface with a forward end and a rearward end. A conical line extends between the forward end to the rear end. A first radius is measured from a centerline of the spinner at substantially 0.25 of a length of the spinner to the conical line. A second radius is also measured at substantially 0.25 of the length and extends outwardly to the outer surface of the spinner. A ratio of the second radius to the first radius is less than or equal to about 2.0. A gas turbine engine is also disclosed.

公开(公告)号：US20190003327A1

公开(公告)日：2019-01-03

申请号：US16123027

申请日：2018-09-06

Applicant: United Technologies Corporation

Inventor： William K. Ackermann ,  Clifton J. Crawley, JR. ,  Frederick M. Schwarz

IPC: F01D11/02 ,  F01D5/08 ,  F16J15/44 ,  F01D11/00 ,  F01D9/06 ,  F01D5/30 ,  F01D11/12 ,  F01D9/04

Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.

公开(公告)号：US10107231B2

公开(公告)日：2018-10-23

申请号：US14753048

申请日：2015-06-29

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F16H57/08 ,  F02K3/06 ,  F02C7/36 ,  F16H57/04

Abstract: A geared architecture for a gas turbine engine comprises a fan shaft and a fan supported on the fan shaft and defining a bypass flow ratio greater than about six. A frame supports the fan shaft. A gear system drives the fan shaft. The gear system has a gear reduction ratio of greater than or equal to about 2.3. A torque frame at least partially supports the gear system. An input is coupled to the gear system. A downstream turbine is coupled to rotatably drive the input coupling. The downstream turbine defines a pressure ratio that is greater than about five (5).

公开(公告)号：US10082105B2

公开(公告)日：2018-09-25

申请号：US15892210

申请日：2018-02-08

Applicant: United Technologies Corporation

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

IPC: F16H57/04 ,  F02K3/06 ,  F02C7/36

CPC classification number: F02K3/06 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/4031 ,  F05D2260/40311 ,  F16H57/0479 ,  F16H57/0486

Abstract: In one exemplary embodiment, a gas turbine engine includes a bypass flow ratio greater than about ten. A fan supported on a fan shaft having a plurality of fan blades and a low fan pressure ratio of less than 1.45 measured across the fan blades alone. A gutter with an annular channel. A gear system connected to the fan shaft having a gear reduction ratio greater than 2.5, planetary gears, and a ring gear with an aperture that is axially aligned with the annular channel. A torque frame at least partially supports the gear system. A low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.