公开(公告)号：US11111818B2

公开(公告)日：2021-09-07

申请号：US16667154

申请日：2019-10-29

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F02C7/32 ,  F02C7/36 ,  F01D15/12 ,  F01D25/28 ,  F01D5/06 ,  F01D9/02 ,  F02K3/06 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F04D19/02 ,  F04D29/056

Abstract: A gas turbine engine includes a fan shaft that drives a fan that has fan blades. An outer housing surrounds the fan. A bypass flow path is within the outer housing. A fan shaft support that supports the fan shaft defines a fan shaft support transverse stiffness. A gear system is connected to the fan shaft. The gear system includes a gear mesh that defines a gear mesh transverse stiffness. A flexible support which supports the gear system relative to a static structure defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 11% of the fan shaft support transverse stiffness. The flexible support transverse stiffness is less than 8% of the gear mesh transverse stiffness.

公开(公告)号：US20210199124A1

公开(公告)日：2021-07-01

申请号：US17196359

申请日：2021-03-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jason Husband ,  James Glaspey

IPC: F04D29/38 ,  F01D5/14 ,  F01D5/18 ,  F04D19/00 ,  F04D29/32 ,  F04D29/64

Abstract: A method for forming a blade for use with a gas turbine engine may include forming a suction side sheath and a pressure side sheath, the suction side sheath and the pressure side sheath forming a continuous sheath that wraps around an interior section of the blade, a first cavity and a second cavity established on opposed sides of a rib, forming a structural core configured for positioning in the interior section between the suction side sheath and the pressure side sheath, the structural core including a first core member, a second core member and a root interconnecting the first and second core members, assembling the suction side sheath and the pressure side sheath with the structural core positioned there between such that the first core member is positioned in the first cavity and such that the second core member is positioned in the second cavity, and securing the suction side sheath to the pressure side sheath to form the blade. A blade for use in a gas turbine engine is also disclosed.

公开(公告)号：US20210363898A1

公开(公告)日：2021-11-25

申请号：US17394497

申请日：2021-08-05

Applicant: Raytheon Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F02C7/32 ,  F02C7/36 ,  F01D15/12 ,  F01D25/28 ,  F01D5/06 ,  F01D9/02 ,  F02K3/06 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F04D19/02 ,  F04D29/056

Abstract: A gas turbine engine includes a fan section that has fan blades that drive air along a bypass flow path in a bypass duct. A fan shaft is drivingly connected to the fan. A turbine section includes a turbine drive shaft. A gear system is connected to the turbine draft shaft through an input and connected to the fan shaft through an output. At least one of the input and the output include a flexible coupling. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the turbine drive shaft during operation. The gear system flex mount arrangement includes a gear mesh that defines a gear mesh lateral stiffness and a ring gear that defines a ring gear lateral stiffness that is less than 12% of the gear mesh lateral stiffness.

公开(公告)号：US20210348515A1

公开(公告)日：2021-11-11

申请号：US17380397

申请日：2021-07-20

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jason Husband ,  James Glaspey ,  Aaron John Pepin

IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28 ,  F01D11/00 ,  F01D5/02

Abstract: A rotor assembly for a gas turbine engine includes a rotatable hub that has a main body and an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels. An array of airfoils are circumferentially distributed about the outer periphery. Each one of the airfoils includes an airfoil section extending from a root section received in the annular channels. Retention pins extend through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach each root section to the hub.

公开(公告)号：US11047337B2

公开(公告)日：2021-06-29

申请号：US15485512

申请日：2017-04-12

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F02K3/06 ,  F02C3/107 ,  F02C7/36 ,  F02C7/20 ,  F01D15/12 ,  F01D5/06 ,  F04D19/00 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F01D9/04

Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.

公开(公告)号：US11021996B2

公开(公告)日：2021-06-01

申请号：US16298319

申请日：2019-03-11

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F02C7/32 ,  F02C7/36 ,  F01D15/12 ,  F01D25/28 ,  F01D5/06 ,  F01D9/02 ,  F02K3/06 ,  F04D25/04 ,  F04D29/053 ,  F04D29/32 ,  F04D19/02 ,  F04D29/056

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. The fan delivers airflow to a bypass duct. A fan shaft support supports the fan shaft and defines a support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input is connected to the gear system and defines a gear system input lateral stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness.