公开(公告)号：US20170292455A1

公开(公告)日：2017-10-12

申请号：US15092008

申请日：2016-04-06

Applicant: General Electric Company

Inventor： Brad Wilson VanTassel ,  Peter Paul Pirolla

IPC: F02C9/18 ,  F02C9/16 ,  F01D25/24 ,  F02C3/04 ,  F02C7/18

CPC classification number: F02C9/18 ,  F01D5/08 ,  F01D5/187 ,  F01D9/065 ,  F01D25/24 ,  F01D25/246 ,  F02C3/04 ,  F02C6/08 ,  F02C7/18 ,  F02C9/16 ,  F02K3/02 ,  F05D2220/32 ,  F05D2250/71 ,  F05D2260/231 ,  F05D2260/606 ,  F05D2260/96 ,  Y02T50/676

Abstract: An air bypass system for a gas turbine engine includes a nozzle for a gas turbine engine. The air bypass system includes the nozzle having an inner band, an outer band, and an airfoil extending between the inner band and the outer band. The airfoil defines an internal passage. A diaphragm includes an inner wall, a first rail, and a second rail, which collectively define a diaphragm cavity. The first rail defines a first rail aperture. A manifold is positioned in the diaphragm cavity. The manifold and the diaphragm collectively define a manifold chamber in fluid communication with the first rail aperture. A tube extends through the internal passage defined by the airfoil and into the diaphragm cavity. The tube is in fluid communication with the manifold chamber. Compressed air flows through the tube into the manifold chamber and exits the chamber through the first rail aperture.

公开(公告)号：US20180016902A1

公开(公告)日：2018-01-18

申请号：US15207750

申请日：2016-07-12

Applicant: General Electric Company

Inventor： Dennis Scott Holloway ,  Adebukola Oluwaseun Benson ,  Melbourne James Myers ,  Peter Paul Pirolla ,  William Scott Zemitis

IPC: F01D5/14 ,  F01D25/24

CPC classification number: F01D5/141 ,  F01D5/145 ,  F05D2250/74 ,  Y02E20/16 ,  Y02T50/673

Abstract: Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

公开(公告)号：US10519873B2

公开(公告)日：2019-12-31

申请号：US15092008

申请日：2016-04-06

Applicant: General Electric Company

Inventor： Brad Wilson VanTassel ,  Peter Paul Pirolla

IPC: F02C9/18 ,  F01D25/24 ,  F02C3/04 ,  F02C7/18 ,  F02C9/16 ,  F01D5/08 ,  F01D5/18 ,  F01D9/06 ,  F02K3/02 ,  F02C6/08

Abstract: An air bypass system for a gas turbine engine includes a nozzle for a gas turbine engine. The air bypass system includes the nozzle having an inner band, an outer band, and an airfoil extending between the inner band and the outer band. The airfoil defines an internal passage. A diaphragm includes an inner wall, a first rail, and a second rail, which collectively define a diaphragm cavity. The first rail defines a first rail aperture. A manifold is positioned in the diaphragm cavity. The manifold and the diaphragm collectively define a manifold chamber in fluid communication with the first rail aperture. A tube extends through the internal passage defined by the airfoil and into the diaphragm cavity. The tube is in fluid communication with the manifold chamber. Compressed air flows through the tube into the manifold chamber and exits the chamber through the first rail aperture.

公开(公告)号：US10247006B2

公开(公告)日：2019-04-02

申请号：US15207750

申请日：2016-07-12

Applicant: General Electric Company

Inventor： Dennis Scott Holloway ,  Adebukola Oluwaseun Benson ,  Melbourne James Myers ,  Peter Paul Pirolla ,  William Scott Zemitis

IPC: F01D5/14 ,  F01D25/24

Abstract: Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

公开(公告)号：US20160319747A1

公开(公告)日：2016-11-03

申请号：US14699055

申请日：2015-04-29

Applicant: General Electric Company

Inventor： Peter Paul Pirolla ,  William Patrick Giffin ,  William Scott Zemitis

IPC: F02C7/18 ,  F01D5/14

CPC classification number: F02C7/18 ,  F01D5/141 ,  F01D5/3007 ,  F05D2220/3212 ,  F05D2230/80 ,  F05D2260/941 ,  F05D2270/114

Abstract: A turbine portion for a gas turbine includes a first stage rotor disk having a plurality of dovetail slots, and a plurality of airfoils coupled to the first stage rotor disk. Each of the plurality of airfoils includes a radial centerline and a blade dovetail mounted in a corresponding one of the plurality of dovetail slots. At least one of the plurality of dovetail slots and the blade dovetail of one of the plurality of airfoils includes a stress reducing backcut spaced between about 1.733-inches (4.402-cm) and about 2.233-inches (5.67-cm) from the radial centerline.

Abstract translation: 用于燃气轮机的涡轮机部分包括具有多个燕尾槽的第一级转子盘和联接到第一级转子盘的多个翼型件。 多个翼型件中的每一个包括安装在多个燕尾槽中的相应一个中的径向中心线和叶片燕尾榫。 所述多个燕尾槽中的至少一个和所述多个翼型中的一个翼片的所述叶片燕尾尾部包括与所述径向中心线相距约1.733英寸（4.402厘米）和约2.233英寸（5.67厘米）间隔的应力减小后刀 。