公开(公告)号：US20170226863A1

公开(公告)日：2017-08-10

申请号：US15019461

申请日：2016-02-09

Applicant: General Electric Company

Inventor： Lee Larned Brozyna ,  Mehmet Suleyman Ciray ,  Mark Andrew Jones

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D5/147 ,  F05D2240/80 ,  F05D2250/73 ,  F05D2250/74 ,  Y02E20/16 ,  Y02T50/673

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket 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; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric endwall contour proximate a junction between the base and the airfoil.

公开(公告)号：US20150037165A1

公开(公告)日：2015-02-05

申请号：US13955679

申请日：2013-07-31

Applicant: General Electric Company

Inventor： Mark Andrew Jones ,  Bradley Taylor Boyer ,  Robert Alan Brittingham ,  Gregory Thomas Foster ,  Christopher William Kester

IPC: F01D5/16 ,  F01D5/14 ,  B23P15/04 ,  F01D5/18

CPC classification number: F01D5/16 ,  B22C9/10 ,  B22C9/24 ,  B23P15/04 ,  F01D5/147 ,  F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F05D2240/304 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  F05D2260/961 ,  Y10T29/49337

Abstract: A turbine blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from pedestals of the second pedestal array by gaps respectively defined therebetween.

Abstract translation: 涡轮叶片被设置并且包括连接以限定冷却剂可通过的内部的压力和吸力表面，以及第一和第二基座阵列，第一和第二基座阵列中的每一个包括基座，分别联接到一个的相应内部面的径向外侧部分 的压力和吸力表面。 第一基座阵列的基座通过分别限定在其间的间隙与第二基座阵列的基座分离。

公开(公告)号：US20140338364A1

公开(公告)日：2014-11-20

申请号：US13894622

申请日：2013-05-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： David Richard Johns ,  Mark Andrew Jones

IPC: F01D5/08

CPC classification number: F01D5/084 ,  F01D5/081 ,  F01D5/187 ,  F01D5/3007 ,  F05D2240/81 ,  F05D2260/201

Abstract: A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting portion. The airfoil portion further defines the cooling circuit. The turbine rotor blade further includes a platform portion that is disposed radially between the mounting portion and the airfoil. The platform portion includes a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls. A cooling plenum that at least partially defines the cooling circuit is defined within the platform portion. The cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls.

Abstract translation: 涡轮转子叶片包括部分地限定涡轮转子叶片内的冷却回路的安装部分和从安装部分径向向外延伸的翼型部分。 机翼部分进一步限定冷却回路。 涡轮转子叶片还包括一个平台部分，其放置在安装部分和翼型件之间。 平台部分包括底壁，顶壁，前壁，后壁和一对相对的侧壁。 至少部分地限定冷却回路的冷却气室限定在平台部分内。 冷却室至少部分地限定在前壁，后壁和一对相对的侧壁之间。