公开(公告)号：US11179895B2

公开(公告)日：2021-11-23

申请号：US16153259

申请日：2018-10-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lawrence Binek ,  Matthew B. Kennedy ,  Evan Butcher ,  Jesse R. Boyer ,  Vijay Narayan Jagdale ,  Dmytro Mykolayovych Voytovych

IPC: B29C64/40 ,  B29C64/153 ,  F01D5/02 ,  F01D21/04 ,  B33Y30/00 ,  B33Y80/00 ,  B33Y10/00

Abstract: A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

公开(公告)号：US11175041B2

公开(公告)日：2021-11-16

申请号：US16598941

申请日：2019-10-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： San Quach ,  John S. Tu ,  Robert M. Sonntag ,  Robert Selinsky, Jr. ,  John J. Rup, Jr. ,  Anthony Van

IPC: F23R3/00

Abstract: A combustor panel of a combustor may include a combustion facing surface, a cooling surface opposite the combustion facing surface, and heat transfer pins extending from the cooling surface. A grouping of the heat transfer pins may include a metallic coating.

公开(公告)号：US11174747B2

公开(公告)日：2021-11-16

申请号：US16819519

申请日：2020-03-16

Applicant: United Technologies Corporation

Inventor： Carson A. Roy Thill ,  Justin K. Bleil ,  Andrew D. Keene ,  Jaime A. Arbona ,  Danielle Mahoney

IPC: F01D25/24 ,  F01D11/08 ,  F01D25/12 ,  F01D5/18 ,  F01D5/20

Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment that has a sealing portion and a pair of opposed rails extending outwardly from the sealing portion. The sealing portion includes a sealing face dimensioned to bound a core flow path and has a backside face opposed to the sealing face. The backside face includes a first localized region, a second localized region between the pair of rails, and a third localized region. A support includes a mounting portion and a first interface portion. At least one retention pin is dimensioned to engage the first interface portion of the support and at least one of the pair of rails such that the seal arc segment is carried by the at least one retention pin. A support plate is arranged relative to the support such that the at least one retention pin is trapped between the support plate and the support. A cooling cavity is established between the support, the support plate, and the second localized region. A method of sealing is also disclosed.

公开(公告)号：US11174737B2

公开(公告)日：2021-11-16

申请号：US16828056

申请日：2020-03-24

Applicant: United Technologies Corporation

Inventor： Robert C. Dolan ,  Michael A. Weisse ,  Daniel A. Bales ,  Steven T. Gordon ,  Dmitri Novikov ,  Eric W. Malmborg ,  Francis B. Parisi

IPC: F01D5/00 ,  F01D5/18

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body defining a recessed region and including at least one rib dimensioned to loop about a respective pocket within a perimeter of the recessed region. At least one cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. The at least one cover skin is welded to the at least one rib along a respective weld path. The weld path defines a weld width, the at least one rib defines a rib width, and a ratio of the weld width to the rib width is equal to or greater than 3:1 for each position along the weld path. A method of forming a gas turbine engine component is also disclosed.

公开(公告)号：US11171976B2

公开(公告)日：2021-11-09

申请号：US16150342

申请日：2018-10-03

Applicant: United Technologies Corporation

Inventor： Paul A. Adamski

IPC: H04L29/06 ,  G06F21/55 ,  G06N5/02

Abstract: A cyber monitored control system includes a controller with a first processing resource operable to execute a control application for a controlled system. The cyber monitored control system also includes a cyber monitor with a second processing resource isolated from the first processing resource. The cyber monitor is operable to evaluate a plurality of inputs to the cyber monitored control system with respect to a cyber threat model, apply trending using the cyber threat model to distinguish between a fault and a cyber attack, and isolate one or more subsystems of the cyber monitored control system based on identifying the cyber attack.

公开(公告)号：US11170140B2

公开(公告)日：2021-11-09

申请号：US16026627

申请日：2018-07-03

Applicant: United Technologies Corporation

Inventor： Daniel A. Snyder ,  Kurt R. Heinemann ,  Glenn Levasseur

IPC: G06F30/20 ,  G06F111/10 ,  G06N20/00

Abstract: A method for qualifying a gas turbine engine component includes creating a first set of substantially identical gas turbine engine components via a uniform manufacturing procedure, determining a set of as-manufactured parameters of each gas turbine engine component in the first set, and determining a variance model of the first set. The variance model includes a representative parameter profile, which includes a plurality of component parameter profiles. The sum of each of the component parameter profiles is the representative parameter profile. The method also includes determining at least one predicted response models based at least in part on the variance model, identifying as-manufactured parameters of a second engine component, applying the as-manufactured parameters of the second engine component to the at least one predicted response models, thereby generating a predicted response output, and qualifying the second engine component for usage in at least one gas turbine engine corresponding to the at least one predicted response model.

公开(公告)号：US11168616B2

公开(公告)日：2021-11-09

申请号：US15980870

申请日：2018-05-16

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Christopher J. Hanlon ,  William G Sheridan

IPC: F02C7/36 ,  F02C6/00 ,  F02C9/00 ,  F02K3/06 ,  F16H1/28 ,  H02K7/116 ,  H02K7/14 ,  H02K7/18

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes among other possible things, a fan section including a plurality of fan blades, a first electric motor assembly that provides a first drive input for driving the fan blades about an axis, a turbine section, and a geared architecture driven by the turbine section and coupled to the fan section to provide a second drive input for driving the fan blades, and second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure controls a speed of the fan blades provided by a combination of the first drive input and the second drive input.

公开(公告)号：US11168574B2

公开(公告)日：2021-11-09

申请号：US16368150

申请日：2019-03-28

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William K. Ackermann

IPC: F01D11/02 ,  F01D11/00 ,  F16J15/44

Abstract: An assembly is provided for rotational equipment. The assembly includes a circumferentially segmented stator and a rotor radially within the stator. The assembly also includes a seal assembly configured for substantially sealing a gap radially between the stator and the rotor. The seal assembly includes a carrier and a non-contact seal seated with the carrier. The carrier includes a plurality of discrete carrier segments circumferentially arranged around the non-contact seal.

公开(公告)号：US11167858B2

公开(公告)日：2021-11-09

申请号：US16126200

申请日：2018-09-10

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  Sorin Bengea

IPC: B64D31/00 ,  B64D41/00 ,  F01D15/10 ,  F01D17/16

Abstract: An aspect includes a variable cycle system of a gas turbine engine. The variable cycle system includes an actuation system, an electric component, and a controller. The actuation system is configured to adjust a variable cycle of turbomachinery of the gas turbine engine. The electric component is operable to provide a shaft power supply or a load corresponding respectively to an adjustment of the turbomachinery. The controller is operable to adjust an output of either or both of the actuation system and the electric component for separate control of thrust and cycle responses.

公开(公告)号：US11156363B2

公开(公告)日：2021-10-26

申请号：US16212791

申请日：2018-12-07

Applicant: United Technologies Corporation

Inventor： Stephen K. Kramer ,  Ryan Lundgreen ,  Robin Prenter

IPC: F23R3/00 ,  F23R3/42

Abstract: A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; and a second component having a first surface, a second surface opposite the first surface of the second component, and a plurality of pin fins extending away from the second surface of the second component, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween, wherein the plurality of pin fins extend into the cooling channel, wherein each of the plurality of pin fins have a pointed ellipse shape.