公开(公告)号：US10794216B2

公开(公告)日：2020-10-06

申请号：US16012059

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D15/10 ,  F02C7/36 ,  F02K3/06 ,  H02K11/00 ,  H02K7/18

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other things, a fan driven by a fan shaft rotatable about an engine axis; a fan drive electric motor providing a supplemental drive input to the fan; a turbine section driving an input shaft; a geared architecture driven by the input shaft of the turbine section and coupled to the fan shaft to provide a main drive input for driving the fan; and a generator including a rotor supported on the input shaft and a stator disposed on a static structure relative to the rotor, wherein the generator communicates electric power to power the fan drive electric motor.

公开(公告)号：US10794193B2

公开(公告)日：2020-10-06

申请号：US15244281

申请日：2016-08-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Mary Colby ,  Paul R Hanrahan ,  Frederick M Schwarz

IPC: F01D5/14 ,  F01D5/28 ,  F04D29/32 ,  F01D25/00

Abstract: An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.

公开(公告)号：US20200240331A1

公开(公告)日：2020-07-30

申请号：US16261688

申请日：2019-01-30

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Coy Bruce Wood

IPC: F02C7/36 ,  F02K3/06 ,  F16H3/72 ,  F01D25/36 ,  F01D15/12 ,  F02C7/275 ,  H02K7/18

Abstract: A turbofan engine includes a first spool including a first turbine, and a first tower shaft engaged to the first spool. A second spool includes a second turbine, and a second tower shaft is engaged to the second spool. A superposition gearbox includes a sun gear, a plurality of intermediate gears engaged to the sun gear, and is supported in a carrier and a ring gear circumscribing the intermediate gears. The first tower shaft or the second tower shaft drives one of the intermediate gears. A drive motor is engaged to drive the sun gear, an inner electric motor, a stator disposed radially outside of the inner electric motor, and an outer electric motor disposed radially outside the stator. A first load on the first spool and a second load on the second spool is adjusted by operation of at least one of the inner electric motor and the outer electric motor.

公开(公告)号：US20190383218A1

公开(公告)日：2019-12-19

申请号：US16012295

申请日：2018-06-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis

IPC: F02C7/18 ,  F02C3/13 ,  F02C6/02

Abstract: A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.

公开(公告)号：US10393067B2

公开(公告)日：2019-08-27

申请号：US15246689

申请日：2016-08-25

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Francis R. Moon ,  Arthur W. Utay

IPC: F02K3/077 ,  F02K3/02 ,  F02K3/06 ,  F02C3/04 ,  F02K3/075 ,  F02C3/10

Abstract: A gas turbine engine includes a spool configured to rotate about an axial centerline. The spool includes a fan rotor and a cold turbine rotor. The fan rotor is rotatably driven by the cold turbine rotor. A cold turbine inlet passage is configured to direct an airflow along a radial inward trajectory to the cold turbine rotor.

公开(公告)号：US10385774B2

公开(公告)日：2019-08-20

申请号：US15268713

申请日：2016-09-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Tania Bhatia Kashyap ,  Mark F. Zelesky ,  Arthur W. Utay ,  Gabriel L. Suciu ,  Thomas N. Slavens ,  Kevin L. Rugg ,  Brian Merry

IPC: F02C3/107 ,  F02C3/14 ,  F02C7/04

Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.

公开(公告)号：US20190186357A1

公开(公告)日：2019-06-20

申请号：US16282891

申请日：2019-02-22

Applicant: United Technologies Corporation

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

IPC: F02C3/113 ,  F02K3/072 ,  F02C9/16 ,  F02K3/06 ,  F02C3/06 ,  F02C7/36

CPC classification number: F02C3/113 ,  F02C3/06 ,  F02C7/36 ,  F02C9/16 ,  F02K3/06 ,  F02K3/072 ,  F05D2200/221 ,  F05D2220/3215 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2270/20

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including fan blades, an outer housing that surrounds the fan to define a bypass flow path, a compressor section in fluid communication with the fan, the compressor section including a low pressure compressor section and a high pressure compressor section, a turbine section including a fan drive turbine section driving the fan and the low pressure compressor section and a high pressure turbine section driving the high pressure compressor section. A gear reduction including an epicyclic gear train is between the fan drive turbine section and the low pressure compressor section such that the low pressure compressor section and the fan are rotatable at a common speed and such that the fan is rotatable at a lower speed than the fan drive turbine section. The fan drive turbine section has a first exit area at a first exit point and is rotatable at a first speed, the high pressure turbine section has a second exit area at a second exit point and is rotatable at a second speed, which is higher than the first speed. A first performance quantity is defined as a product of the first speed squared and the first area, a second performance quantity is defined as a product of the second speed squared and the second exit area and a performance ratio of the first performance quantity to the second performance quantity is between 0.2 and 0.8.

公开(公告)号：US20190153960A1

公开(公告)日：2019-05-23

申请号：US16186811

申请日：2018-11-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C7/36 ,  F02C3/107 ,  F01D1/26 ,  F02K3/06 ,  F01D15/12

CPC classification number: F02C7/36 ,  F01D1/26 ,  F01D15/12 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/40311 ,  F05D2270/051

Abstract: A gas turbine engine turbine has a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, the high pressure turbine rotatable with the high pressure compressor as a high pressure spool in a first direction about an engine longitudinal axis, the low pressure turbine rotatable as a low pressure spool in the first direction about the engine longitudinal axis, a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, a fan section including a fan having a plurality of fan blades, the fan connected to the low pressure spool via a geared architecture such that the fan is rotatable about the engine longitudinal axis in a second direction opposed to the first direction, and a bypass ratio greater than 6.

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：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.