Turbine bucket having tip shroud fillet, tip shroud cross-drilled apertures and profile

Patent metadata

Field	Value
Publication number	US-10697308-B2
Application number	US-201816170523-A
Country	US
Kind code	B2
Filing date	Oct 25, 2018
Priority date	Feb 9, 2016
Publication date	Jun 30, 2020
Grant date	Jun 30, 2020

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; a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge; and a tip shroud connected with a second end of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, the tip shroud including a tip shroud fillet connecting the airfoil and the tip shroud and having a non-uniform thickness across an axial length of the airfoil.

First claim

We claim:

1. A turbine bucket comprising:
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;
a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge; and
a tip shroud connected with a second end of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, the tip shroud including a tip shroud fillet connecting the airfoil and the tip shroud and having a non-uniform thickness across an axial length of the airfoil,
wherein the tip shroud fillet has a non-uniform thickness across an axial chord length of the airfoil as defined by: a first section having a first thickness and a second section having a second, greater thickness, wherein the second section spans between approximately 20 percent of the axial chord length of the airfoil and approximately 50 percent of the axial chord length of the airfoil,
wherein the tip shroud includes a set of cross-drilled apertures, the set of cross-drilled apertures being smaller than primary cooling apertures extending entirely radially through the tip shroud, wherein the set of cross-drilled apertures are oriented at a divergent angle relative to the primary cooling apertures extending radially through the tip shroud, wherein the primary cooling apertures extend entirely radially through the tip shroud and the set of cross-drilled apertures outlet at a radially outer surface of the tip shroud.

2. The turbine bucket of claim 1 , further comprising a fillet connecting a surface of the base to a surface of the airfoil.

3. The turbine bucket of claim 1 , wherein the turbine bucket includes a third stage bucket.

4. The turbine bucket of claim 1 , wherein the base directs flow of a working fluid across a passage trough proximate the suction side of the airfoil.

5. The turbine bucket of claim 1 , wherein the base is radially inboard of the airfoil.

Assignees

• Gen Electric

Inventors

• Ristau Neil
• Taylor Zachary James
• Weber David Wayne

Classifications

• F01D5/225 Primary

  by shrouding · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• Y02E20/16

  Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT] · CPC title

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title