公开(公告)号：US09976560B2

公开(公告)日：2018-05-22

申请号：US14189067

申请日：2014-02-25

Applicant: Greenheck Fan Corporation

Inventor： Kyle Andrew Brownell

IPC: F04D25/06 ,  F04D29/34 ,  F04D29/52 ,  F04D29/02 ,  F04D29/30 ,  F04D29/62 ,  F04D29/60

CPC classification number: F04D25/06 ,  F04D29/023 ,  F04D29/30 ,  F04D29/601 ,  F04D29/626 ,  F05D2230/24 ,  F05D2300/121

Abstract: Fan assemblies, and in particular fan wheels and stator assemblies for fan assemblies, are disclosed. In one embodiment, the fan wheel includes a wheel back having an outer surface forming one of a curved dome-shape and a truncated cone-shape. The fan wheel may also include a plurality of fan blades radially spaced about and mounted to the outer surface of the wheel back. In one embodiment, each of the fan blades is formed from a segment of an airfoil-shaped aluminum extrusion defining at least one internal cavity. The fan blade first ends can be provided with a compound cut profile with at least one curved cut such that the first end of the blade is mounted flush to the wheel back outer surface. The stator assembly can also be provided with a plurality of stator blades formed from airfoil-shaped aluminum extrusion segments and provided with compound cut profiles.

公开(公告)号：US09970297B2

公开(公告)日：2018-05-15

申请号：US14832296

申请日：2015-08-21

Applicant: Rolls-Royce Corporation

Inventor： Wade A. Vest

IPC: F01D5/30 ,  F01D5/02 ,  C25D1/02 ,  C25D1/08 ,  C25D5/56 ,  F04D29/32 ,  F01D25/00 ,  F04D29/02 ,  F01D5/32

CPC classification number: F01D5/02 ,  C25D1/02 ,  C25D1/08 ,  C25D5/56 ,  F01D5/323 ,  F01D25/005 ,  F04D29/023 ,  F04D29/322 ,  F05D2220/36 ,  F05D2230/24 ,  F05D2230/90 ,  F05D2250/191 ,  F05D2300/17 ,  F05D2300/433 ,  F05D2300/436 ,  F05D2300/605 ,  Y02T50/671 ,  Y02T50/672

Abstract: A fan slider for use in a fan assembly to push a fan blade radially outward of a rotating axis of the gas turbine engine. The fan slider may include a fan slider body coated with a nanocrystalline metallic coating and a slider spring.

公开(公告)号：US06582195B2

公开(公告)日：2003-06-24

申请号：US09891513

申请日：2001-06-27

Applicant: Dwight Eric Davidson

Inventor： Dwight Eric Davidson

IPC: F01D530

CPC classification number: F01D5/323 ,  F01D5/30 ,  F01D5/3069 ,  F01D11/005 ,  F05D2230/24 ,  F05D2230/64 ,  F05D2260/30

Abstract: An integral compressor rotor spacer cartridge fits within the dovetail region of the rim of a compressor rotor wheel to retain the dovetail portion of the rotor blade and maintain an angular spaced relationship between the rotor blades. The dovetail portion of the rotor blade is retained in a pocket or notched portion of the spacer cartridge.

Abstract translation: 一体的压缩机转子间隔器盒装配在压缩机转子轮的边缘的燕尾区域内，以保持转子叶片的燕尾部分并保持转子叶片之间的角度间隔的关系。 转子叶片的燕尾部分保持在间隔盒的口袋或凹口部分中。

公开(公告)号：US5927130A

公开(公告)日：1999-07-27

申请号：US961818

申请日：1997-10-31

Applicant: Thomas J. Watson ,  Vincent C. Nardone ,  John A. Visoskis ,  Stuart A. Anderson

Inventor： Thomas J. Watson ,  Vincent C. Nardone ,  John A. Visoskis ,  Stuart A. Anderson

IPC: B21C23/00 ,  F01D5/14 ,  F01D5/28 ,  F01D9/02 ,  B21C25/04

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2230/24 ,  F05D2300/173 ,  F05D2300/603 ,  Y10T29/49337 ,  Y10T29/49339

Abstract: A method for manufacturing an airfoil is provided which includes the steps of: a) providing a billet of discontinuously reinforced aluminum having at least 10 volume percent of silicon carbide as a reinforcing element, and no more than 30 volume percent of silicon carbide as the reinforcing element; 2) extruding the billet into an airfoil shaped geometry from a die, wherein the geometry includes a first wall, a second wall disposed opposite the first wall, a leading edge, a trailing edge disposed opposite the leading edge, and a first cavity disposed between the first and second walls, and the leading and trailing edges.

Abstract translation: 提供一种用于制造翼型的方法，其包括以下步骤：a）提供具有至少10体积％的碳化硅作为增强元素的不连续增强的铝坯料，并且不超过30体积％的碳化硅作为增强材料 元件; 2）将坯料从模具中挤出成翼型几何形状，其中几何形状包括第一壁，与第一壁相对设置的第二壁，前缘，与前缘相对设置的后缘，以及设置在 第一和第二壁，以及前缘和后缘。

公开(公告)号：US5902546A

公开(公告)日：1999-05-11

申请号：US854163

申请日：1997-05-09

Applicant: Nozomu Kawasetsu ,  Masatomo Shinohara ,  Kouichiro Imakiire ,  Masanori Kimura ,  Keiichi Shiraishi ,  Masayuki Hayakawa ,  Kazuhisa Shibue ,  Yoshimasa Okubo ,  Naoki Tokizane

Inventor： Nozomu Kawasetsu ,  Masatomo Shinohara ,  Kouichiro Imakiire ,  Masanori Kimura ,  Keiichi Shiraishi ,  Masayuki Hayakawa ,  Kazuhisa Shibue ,  Yoshimasa Okubo ,  Naoki Tokizane

IPC: F01D5/04 ,  B21K1/36 ,  C22C1/04 ,  C22C21/00 ,  C23C4/12 ,  F02B39/00 ,  F04D29/02 ,  F04D29/28 ,  F04D29/30 ,  F02B37/00

CPC classification number: B21K1/36 ,  C22C1/0416 ,  C22C21/00 ,  C23C4/123 ,  F04D29/023 ,  F04D29/284 ,  F05D2230/24 ,  F05D2230/25 ,  F05D2230/42 ,  F05D2300/173 ,  F05D2300/518 ,  F05D2300/609

Abstract: There is disclosed a high heat resistant aluminum alloy impeller, which is suitably used as an impeller, especially for a centrifugal compressor, and for the rotor and the blade of a turbo molecular pump or the scroll of a scroll compressor. Also, a method for manufacturing this aluminum alloy impeller is disclosed. The impeller is composed of an Al--Fe rapid solidification aluminum alloy, which is produced by a spray forming process for spraying a molten metal with inert gas and rapidly solidifying the metal at a cooling speed of 10.sup.2 .degree. C./sec. or higher while simultaneously deposing the metal. The rapid solidification aluminum alloy is subjected to hot extrusion processing within a temperature range of 200.degree. C. to 600.degree. C. and further subjected to hot forging.

Abstract translation: 公开了一种高耐热铝合金叶轮，其适合用作叶轮，特别用于离心式压缩机，以及涡轮分子泵的转子和叶片或涡旋压缩机的涡旋。 此外，公开了一种用于制造该铝合金叶轮的方法。 叶轮由Al-Fe快速凝固铝合金组成，其通过用惰性气体喷射熔融金属并以102℃/秒的冷却速度快速固化的喷射成形方法制造。 或更高，同时使金属脱落。 快速凝固铝合金在200〜600℃的温度范围内进行热挤压加工，并进一步进行热锻。

公开(公告)号：US2914841A

公开(公告)日：1959-12-01

申请号：US61387156

申请日：1956-10-04

Applicant: INT NICKEL CO

Inventor： GRAHAM ALEXANDER B

IPC: B21C23/16 ,  B23P15/02 ,  F01D5/18

CPC classification number: B21C23/16 ,  B23P15/02 ,  F01D5/187 ,  F05D2230/24 ,  Y10T29/49341

公开(公告)号：US11988095B2

公开(公告)日：2024-05-21

申请号：US17685953

申请日：2022-03-03

Applicant: General Electric Company

Inventor： Deepak Trivedi ,  Rahul Anil Bidkar ,  Uttara Vijay Kumar

IPC: F01D11/00 ,  F01D11/04 ,  F01D25/28 ,  F16J15/40 ,  B33Y80/00

CPC classification number: F01D11/001 ,  F01D11/04 ,  F01D25/28 ,  B33Y80/00 ,  F05D2230/24 ,  F05D2230/31 ,  F05D2240/55 ,  F05D2250/73 ,  F05D2260/38 ,  F05D2300/50212 ,  F05D2300/603

Abstract: A seal assembly for a component of a turbomachine and method of assembly thereof is provided. The seal assembly includes at least one mating face positioned adjacent to the component and a seal coupled to the mating face. The seal includes an outer shell defining an interior space; an inner matrix filling the interior space comprising a plurality of unit cells comprising one or more metamaterials, wherein at least a portion of the plurality of unit cells are identical, and wherein the plurality of unit cells are repeated throughout the inner matrix; and one or more support struts extending throughout the inner matrix. The method of building the seal assembly may include selecting a first material for the outer shell and selecting the one or more metamaterials for the inner matrix based on the first material.

公开(公告)号：US20190211752A1

公开(公告)日：2019-07-11

申请号：US16354351

申请日：2019-03-15

Applicant: DENSO CORPORATION

Inventor： Etsugo YANAGIDA ,  Tetsuji YAMANAKA ,  Naoaki KONO

IPC: F02C9/18 ,  F02C3/00

CPC classification number: F02C9/18 ,  F02B37/18 ,  F02B39/00 ,  F02C3/00 ,  F05D2230/24 ,  F05D2270/021 ,  Y02T10/144

Abstract: A turbocharger includes a FIGwastegate valve, an actuator for the wastegate valve, and a link mechanism linking the wastegate valve with the actuator via a specific rod. A plate is a component of the link mechanism and connects the wastegate valve with the rod or connects the rod with the actuator. The plate includes a body portion in a plate shape and a pin portion protruding from the main body portion. The pin portion is in a tubular shape having a hollow portion opened to its outside. The pin portion is engageable with an other component of the link mechanism on its outer periphery to form a rotation axis of the other component.

公开(公告)号：US09027245B2

公开(公告)日：2015-05-12

申请号：US13805126

申请日：2011-06-23

Applicant: Christine Hottier ,  Bertrand Lamaison ,  Jacques Abousefian

Inventor： Christine Hottier ,  Bertrand Lamaison ,  Jacques Abousefian

IPC: B21K1/74 ,  B21K3/04 ,  B23P15/04 ,  F01D5/14 ,  F01D5/28 ,  F04D29/02 ,  F04D29/32 ,  F01D5/00 ,  B29C65/00 ,  B29L31/08 ,  B29C65/48

CPC classification number: B21K3/04 ,  B23P15/04 ,  B29C65/48 ,  B29C65/483 ,  B29C65/484 ,  B29C66/12461 ,  B29C66/12463 ,  B29C66/301 ,  B29C66/53 ,  B29C66/721 ,  B29C66/742 ,  B29L2031/08 ,  B29L2031/082 ,  F01D5/00 ,  F01D5/147 ,  F01D5/282 ,  F01D5/286 ,  F04D29/023 ,  F04D29/324 ,  F05D2230/24 ,  F05D2230/25 ,  F05D2240/303 ,  F05D2300/702 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49336

Abstract: A method for producing a solid component which in succession includes deforming a metal bar by forging using two dies in order to obtain an intermediate component including two fins one on each side of a solid part capable of forming the base of the metal reinforcement, the two fins being at a divergent angle α; deforming the two fins of the intermediate component, altering the divergent angle α, so as to obtain the final shape of the turbomachine blade leading edge or trailing edge metal reinforcement.

Abstract translation: 一种固体成分的制造方法，其特征在于，包括通过使用两个模具进行锻造使金属棒变形，以获得包括两个翅片的中间部件，所述中间部件在能够形成所述金属加强件的基部的实心部分的每一侧上，所述两个 翅片处于发散角α; 使中间部件的两个翅片变形，改变发散角α，以获得涡轮机叶片前缘或后缘金属加强件的最终形状。

公开(公告)号：US5873699A

公开(公告)日：1999-02-23

申请号：US670302

申请日：1996-06-27

Applicant: Thomas J. Watson ,  Vincent C. Nardone ,  John A. Visoskis ,  Stuart A. Anderson

Inventor： Thomas J. Watson ,  Vincent C. Nardone ,  John A. Visoskis ,  Stuart A. Anderson

IPC: B21C23/00 ,  F01D5/14 ,  F01D5/28 ,  F01D9/02 ,  F01D1/02

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2230/24 ,  F05D2300/173 ,  F05D2300/603 ,  Y10T29/49337 ,  Y10T29/49339

Abstract: An airfoil is provided having a cross-sectional geometry which includes a first wall, a second wall disposed opposite the first wall, a leading edge, a trailing edge disposed opposite the leading edge, and a first cavity. The first cavity is disposed between the first and second walls, and the leading and trailing edges. The cross-sectional geometry extends between a first and a second end, and the airfoil is formed from discontinuously reinforced aluminum.

Abstract translation: 提供一种翼型件，其横截面几何形状包括第一壁，与第一壁相对设置的第二壁，前缘，与前缘相对设置的后缘和第一腔。 第一腔设置在第一和第二壁之间以及前缘和后缘之间。 横截面几何形状在第一和第二端之间延伸，翼型由不连续增强的铝形成。