公开(公告)号：US20230093292A1

公开(公告)日：2023-03-23

申请号：US17478132

申请日：2021-09-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Martin DOBSON ,  Oleg ISKRA ,  Michael FRYER ,  Marc LAVOIE ,  Ivan Sidorovich PARADISO ,  Louis DURANLEAU-HENDRICKX ,  Domenico DI FLORIO ,  Tibor URAC

IPC: F02C9/18 ,  F02C6/08

Abstract: The gas turbine engine can have a pneumatic actuator; an intake device secured to a gas path wall delimiting the gas path, the intake device having a tubular body protruding from the gas path wall into the gas path and an inlet aperture formed in the tubular body, the inlet aperture spaced-apart from the gas path wall and facing downstream relative a flow orientation of the gas path, the intake device having an internal conduit extending from the inlet aperture, along the tubular body, to an outlet across the gas path wall; and a fluid line fluidly connecting the outlet of the intake device to the pneumatic actuator.

公开(公告)号：US20240229739A1

公开(公告)日：2024-07-11

申请号：US18151721

申请日：2023-01-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Yashiva DORSAMY ,  Domenico DI FLORIO

IPC: F02K1/48 ,  F02K1/38

CPC classification number: F02K1/48 ,  F02K1/386 ,  F05D2220/323

Abstract: An aircraft engine including a core casing defining a core passage, a nacelle located radially outward from and circumferentially around the casing, and a bypass passage radially defined between nacelle and casing. A mixer mounted to the casing, including a wall having a leading edge attached to casing and defining a plurality of lobes that are circumferentially spaced apart. A damper ring surrounds the mixer at an axial location between leading edge and trailing edge of the wall, and extends circumferentially uninterrupted, and extends axially from first side to second side. The first side being spaced axially away from the leading edge, and the damper ring having an annular ring surface extending between the first and second sides and second side. The damper ring is radially mounted to the mixer wall via an annular ring surface to dampen the wall.

公开(公告)号：US20180051634A1

公开(公告)日：2018-02-22

申请号：US15240418

申请日：2016-08-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Domenico DI FLORIO ,  Eric HOSKING

IPC: F02C7/28 ,  F16J15/02 ,  F02C7/06 ,  F02C7/22

Abstract: A system comprises a pipe defining a fluid passage, the pipe having a first rate of thermal expansion. A housing defines an opening for receiving an end of the pipe for fluid circulation between the fluid passage and an interior of the housing, the housing having a second rate of thermal expansion lesser than the first rate of thermal expansion, at least one annular gap defined between a periphery of the opening and the end of the pipe when the system is below a safety condition threshold temperature. Seal(s) seal the annular gap, wherein the pipe and the housing are configured and the first and second rates of thermal expansion are selected so that, when the system exceeds the safety condition threshold temperature, the end of the pipe contacts the periphery of the opening by thermal expansion to seal the annular gap independent of the at least one seal.

公开(公告)号：US20160251963A1

公开(公告)日：2016-09-01

申请号：US14633503

申请日：2015-02-27

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Marc TARDIF ,  Domenico DI FLORIO ,  Aldo ABATE

IPC: F01D5/10

CPC classification number: F01D5/10 ,  F01D5/22 ,  F01D5/3007 ,  F05D2220/32 ,  F05D2260/96

Abstract: A rotor blade vibration damper for a gas turbine engine includes an elongated damper body including a top portion extending longitudinally between a front end and a rear end. The top portion has a width defined between spaced apart lateral sides and is substantially flat between the front and rear ends and between the lateral sides such as to define a longitudinal plane within which the top portion lies. A front tab extends downwardly from the front end of the top portion relative to the longitudinal plane. The rear end of the top portion is flat and generally contained in the longitudinal plane. A pair of lateral tabs extends downwardly from each of said lateral sides of the top portion relative to the longitudinal plane.

Abstract translation: 用于燃气涡轮发动机的转子叶片减振器包括细长的阻尼器主体，其包括在前端和后端之间纵向延伸的顶部。 顶部具有限定在间隔开的横向侧面之间的宽度，并且在前端和后端之间以及横向侧之间基本上是平坦的，以便限定顶部部分所在的纵向平面。 前突片相对于纵向平面从顶部的前端向下延伸。 顶部的后端是平的，并且通常包含在纵向平面中。 一对横向突片相对于纵向平面从顶部的所述横向侧边中的每一个向下延伸。

公开(公告)号：US20240229738A1

公开(公告)日：2024-07-11

申请号：US18151715

申请日：2023-01-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Yashiva DORSAMY ,  Domenico DI FLORIO

IPC: F02K1/48

CPC classification number: F02K1/48 ,  F05D2220/323 ,  F05D2300/506

Abstract: An aircraft engine including a core casing extending circumferentially about an axis and defining a core flow passage, a nacelle located radially outward from and around the casing, and a bypass passage defined between the nacelle and the casing. A mixer includes a peripheral wall having a leading edge and a trailing edge, the leading edge attached to the casing. A first mixer portion and a second mixer portion are circumferentially spaced apart and respectively extend away from the leading edge from a first location to a second location. The first and second mixer portions respectively have a first and second stiffness, the first stiffness greater than the second stiffness and greater than a stiffness of an upstream portion of the wall extending from the first mixer portion at the first location toward the leading edge.

公开(公告)号：US20230029960A1

公开(公告)日：2023-02-02

申请号：US17389450

申请日：2021-07-30

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Martin DOBSON ,  Oleg ISKRA ,  Michael FRYER ,  Marc LAVOIE ,  Ivan SIDOROVICH PARADISO ,  Louis DURANLEAU-HENDRICKX ,  Domenico DI FLORIO ,  Tibor URAC

IPC: F02C6/08 ,  F02C3/00

Abstract: An orifice pack is provided for delivering pressurized air to a compressor bleed valve of a gas turbine engine. The orifice pack has a diffusion chamber in serial flow communication with a tapering passage and a first outlet passage for venting a first portion of the pressurized air from the diffusion chamber. A second outlet passage branches off from the diffusion chamber at an axial location between the inlet and the tapering passage. The second outlet passage is fluidly connected to the compressor bleed valve for directing a second portion of the pressurized air from the diffusion chamber to the compressor bleed valve.

公开(公告)号：US20220412259A1

公开(公告)日：2022-12-29

申请号：US17358196

申请日：2021-06-25

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Martin DOBSON ,  Oleg ISKRA ,  Michael FRYER ,  Marc LAVOIE ,  Ivan SIDOROVICH PARADISO ,  Louis DURANLEAU-HENDRICKX ,  Domenico DI FLORIO

IPC: F02C7/05 ,  F02C9/18

Abstract: Methods and systems for filtering pressurized air used to control a compressor bleed valve of a gas turbine engine are provided. One method comprises receiving the pressurized air in a conduit via an inlet of the conduit, releasing a first portion of the pressurized air out of the conduit via an outlet of the conduit, releasing a second portion of the pressurized air from the conduit via a port disposed between the inlet and the outlet of the conduit, directing the second portion of the pressurized air from the port to a filter along an upward flow path, filtering the second portion of the pressurized air using the filter, and directing the second portion of the pressurized air from the filter toward the compressor bleed valve.