公开(公告)号：US07476082B2

公开(公告)日：2009-01-13

申请号：US11209013

申请日：2005-08-22

Applicant: Costas Vogiatzis ,  Maitreya Madhyastha ,  Steven Don Arnold

Inventor： Costas Vogiatzis ,  Maitreya Madhyastha ,  Steven Don Arnold

IPC: F04D29/30

CPC classification number: F01D17/165 ,  F05D2220/40 ,  Y10S416/02

Abstract: Exemplary turbine blade outer edges, exemplary vane inner edges, exemplary systems and exemplary methods are disclosed that help to reduce noise in variable geometry turbines and optionally other turbines wherein a turbine blade interacts with an object. Other exemplary turbine-related technologies are also disclosed.

Abstract translation: 公开了示例性的涡轮叶片外边缘，示例性叶片内边缘，示例性系统和示例性方法，其有助于降低可变几何涡轮机中的噪声，并且可选地，其中涡轮机叶片与物体相互作用的其它涡轮机。 还公开了其它示例性的涡轮机相关技术。

公开(公告)号：US20080260533A1

公开(公告)日：2008-10-23

申请号：US11209013

申请日：2005-08-22

Applicant: Costas Vogiatzis ,  Maitreya Madhyastha ,  Steven Don Arnold

Inventor： Costas Vogiatzis ,  Maitreya Madhyastha ,  Steven Don Arnold

IPC: F04D29/30

CPC classification number: F01D17/165 ,  F05D2220/40 ,  Y10S416/02

Abstract: Exemplary turbine blade outer edges, exemplary vane inner edges, exemplary systems and exemplary methods are disclosed that help to reduce noise in variable geometry turbines and optionally other turbines wherein a turbine blade interacts with an object. Other exemplary turbine-related technologies are also disclosed.

Abstract translation: 公开了示例性的涡轮叶片外边缘，示例性叶片内边缘，示例性系统和示例性方法，其有助于降低可变几何涡轮机中的噪声，并且可选地，其中涡轮叶片与物体相互作用的其它涡轮机。 还公开了其它示例性的涡轮机相关技术。

公开(公告)号：US07255530B2

公开(公告)日：2007-08-14

申请号：US11007769

申请日：2004-12-08

Applicant: Costas Vogiatzis ,  Nidal A. Ghizawi

Inventor： Costas Vogiatzis ,  Nidal A. Ghizawi

IPC: F01D17/16

CPC classification number: F01D17/165 ,  F01D5/141 ,  F01D9/02 ,  F05D2220/40 ,  F05D2250/70

Abstract: An exemplary vane for a radial turbine assembly includes a hub end and a shroud end that define vane height, a leading edge and a trailing edge that define vane length along a camberline and an inner surface and an outer surface that extend from the hub end to the shroud end and meet at the leading edge and the trailing edge and that define vane thickness wherein, for at least a portion of the vane, vane length and vane thickness vary with respect to vane height. Other exemplary vanes, assemblies, methods, etc., are also disclosed.

Abstract translation: 用于径向涡轮组件的示例性叶片包括轮毂端和限定叶片高度的护罩端部，前缘和后缘，其沿着弯曲线限定叶片长度，并且内表面和外表面从轮毂端延伸到 护罩端部并且在前缘和后缘处相遇并且限定叶片厚度，其中对于叶片的至少一部分，叶片长度和叶片厚度相对于叶片高度变化。 还公开了其它示例性叶片，组件，方法等。

公开(公告)号：US07484935B2

公开(公告)日：2009-02-03

申请号：US11144472

申请日：2005-06-02

Applicant: Gregory B. Heitland ,  Costas Vogiatzis

Inventor： Gregory B. Heitland ,  Costas Vogiatzis

IPC: F01D5/30

CPC classification number: F01D5/143 ,  F05D2250/70 ,  F05D2250/71 ,  Y02T50/673

Abstract: Disclosed herein is a turbine rotor having a contoured hub comprising a cambered surface extending from a leading edge of the rotor hub to a trailing edge of the rotor hub along an axial direction of the rotor hub. A turbine rotor and a gas turbine engine comprising a turbine rotor flow path having a cambered surface are also disclosed, together with a method providing a turbine rotor flow path for a turbine rotor hub.

Abstract translation: 这里公开了一种涡轮转子，其具有轮廓轮毂，其包括从转子毂的前缘延伸到转子毂的后缘的弧形表面沿着转子毂的轴向方向。 还公开了一种包括具有弧形表面的涡轮转子流动路径的涡轮转子和燃气涡轮发动机，以及为涡轮机转子毂提供涡轮转子流动路径的方法。

公开(公告)号：US20050220616A1

公开(公告)日：2005-10-06

申请号：US11007769

申请日：2004-12-08

Applicant: Costas Vogiatzis ,  Nidal Ghizawi

Inventor： Costas Vogiatzis ,  Nidal Ghizawi

IPC: F01D5/14 ,  F01D9/02 ,  F01D17/16

CPC classification number: F01D17/165 ,  F01D5/141 ,  F01D9/02 ,  F05D2220/40 ,  F05D2250/70

Abstract: An exemplary vane for a radial turbine assembly includes a hub end and a shroud end that define vane height, a leading edge and a trailing edge that define vane length along a camberline and an inner surface and an outer surface that extend from the hub end to the shroud end and meet at the leading edge and the trailing edge and that define vane thickness wherein, for at least a portion of the vane, vane length and vane thickness vary with respect to vane height. Other exemplary vanes, assemblies, methods, etc., are also disclosed.

Abstract translation: 用于径向涡轮组件的示例性叶片包括轮毂端和限定叶片高度的护罩端部，前缘和后缘，其沿着弯曲线限定叶片长度，并且内表面和外表面从轮毂端延伸到 护罩端部并且在前缘和后缘处相遇并且限定叶片厚度，其中对于叶片的至少一部分，叶片长度和叶片厚度相对于叶片高度变化。 还公开了其它示例性叶片，组件，方法等。

公开(公告)号：US06948907B2

公开(公告)日：2005-09-27

申请号：US10430464

申请日：2003-05-05

Applicant: Costas Vogiatzis ,  Maitreya Madhyastha ,  Steven Don Arnold

Inventor： Costas Vogiatzis ,  Maitreya Madhyastha ,  Steven Don Arnold

IPC: F01D17/16

CPC classification number: F01D17/165 ,  F05D2220/40 ,  Y10S416/02

Abstract: Exemplary turbine blade outer edges, exemplary vane inner edges, exemplary systems and exemplary methods are disclosed that help to reduce noise in variable geometry turbines and optionally other turbines wherein a turbine blade interacts with an object. Other exemplary turbine-related technologies are also disclosed.

Abstract translation: 公开了示例性的涡轮叶片外边缘，示例性叶片内边缘，示例性系统和示例性方法，其有助于降低可变几何涡轮机中的噪声，并且可选地，其中涡轮叶片与物体相互作用的其它涡轮机。 还公开了其它示例性的涡轮机相关技术。

公开(公告)号：US06709232B1

公开(公告)日：2004-03-23

申请号：US10236281

申请日：2002-09-05

Applicant: Costas Vogiatzis

Inventor： Costas Vogiatzis

IPC: F01D1716

CPC classification number: F01D17/165 ,  F01D5/141 ,  F05D2220/40

Abstract: Improved cambered vanes are constructed for use within a vaned turbocharger and comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane inner and outer airfoil surfaces, in conjunction with the vane leading edge, are specifically configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, that has a gradually curved section and a substantially flat section. The vanes have characteristic camberlines that are flat for at least about the first 5 percent of the vane length, moving away from the vane leading edge, for reducing unwanted aerodynamic effects within the turbine housing, thereby increasing turbocharger and turbocharged engine operations.

Abstract translation: 改进的弧形叶片被构造用于在涡轮增压器内使用，并且包括邻近涡轮机叶轮定向的内部翼型件表面，以及与内部翼型件表面相对定向的外部翼型件表面。 内翼面和外翼面限定叶片翼型厚度。 弧形叶片前缘或鼻子沿着第一内部和外部翼型表面接合部定位，并且沿第二内部和外部表面接合部设置的叶片后缘。 叶片内外翼表面与叶片前缘一起被特别地构造成提供叶片弯度线，其在翼型件表面之间测量并且沿着叶片的长度延伸，其具有逐渐弯曲的部分和基本平坦的部分 。 叶片具有平滑的特征曲线，至少大约叶片长度的前5％，远离叶片前缘移动，以减少涡轮机壳体内的不必要的空气动力学效应，从而增加涡轮增压器和涡轮增压发动机的运行。

公开(公告)号：US20110250046A1

公开(公告)日：2011-10-13

申请号：US12755932

申请日：2010-04-07

Applicant: Costas Vogiatzis ,  Ramakumar Venkata Naga Bommisetty ,  Jwala Singh

Inventor： Costas Vogiatzis ,  Ramakumar Venkata Naga Bommisetty ,  Jwala Singh

IPC: F04D27/02 ,  F04D31/00

CPC classification number: F01D21/14 ,  F02C6/08 ,  F02C7/05

Abstract: Methods and apparatus are provided for improving engine performance in a turbofan gas turbine engine following foreign object ingestion in turbofan gas turbine engines that include an intake fan that includes a plurality of fan blades, and that is disposed within and surrounded by a fan case. The occurrence of a foreign object ingestion by the turbofan gas turbine engine is detected and, upon detecting that a foreign object has been ingested, air is bled from a region proximate the blades of the intake fan through a slot in the fan case.

Abstract translation: 提供的方法和装置用于在涡轮风扇燃气涡轮发动机中异物摄取之后改进涡轮风扇燃气涡轮发动机中的发动机性能，所述涡轮风扇燃气涡轮发动机包括包括多个风扇叶片的进气扇，并且设置在风扇壳体内并被其包围。 检测到涡轮风扇燃气轮机引起异物摄入的发生，并且在检测到异物被摄取后，通过风扇壳体中的狭槽从进气扇的叶片附近的区域排出空气。

公开(公告)号：US20060275126A1

公开(公告)日：2006-12-07

申请号：US11144472

申请日：2005-06-02

Applicant: Gregory Heitland ,  Costas Vogiatzis

Inventor： Gregory Heitland ,  Costas Vogiatzis

IPC: F01D11/00

CPC classification number: F01D5/143 ,  F05D2250/70 ,  F05D2250/71 ,  Y02T50/673

Abstract: Disclosed herein is a turbine rotor having a contoured hub comprising a cambered surface extending from a leading edge of the rotor hub to a trailing edge of the rotor hub along an axial direction of the rotor hub. A turbine rotor and a gas turbine engine comprising a turbine rotor flow path having a cambered surface are also disclosed, together with a method providing a turbine rotor flow path for a turbine rotor hub.

公开(公告)号：US07001143B2

公开(公告)日：2006-02-21

申请号：US10795075

申请日：2004-03-05

Applicant: Costas Vogiatzis

Inventor： Costas Vogiatzis

IPC: F01D17/16

CPC classification number: F01D17/165 ,  F01D5/141 ,  F05D2220/40

Abstract: Improved cambered vanes comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane airfoil surfaces, in conjunction with the vane leading edge, are specifically configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, having a gradually curved section and a substantially flat section.

Abstract translation: 改进的弧形叶片包括邻近涡轮机叶轮定向的内部翼面表面和与内部翼型表面相对定向的外部翼型件表面。 内翼面和外翼面限定叶片翼型厚度。 弧形叶片前缘或鼻子沿着第一内部和外部翼型表面接合部定位，并且沿第二内部和外部表面接合部设置的叶片后缘。 叶片翼型件表面与叶片前缘一起被特别地构造成提供叶片弯度线，其在翼型件表面之间测量并沿着叶片的长度延伸，具有逐渐弯曲的部分和基本平坦的部分。