Turbine blade attachment curved rib stiffeners

Patent metadata

Field	Value
Publication number	US-2017218776-A1
Application number	US-201615009366-A
Country	US
Kind code	A1
Filing date	Jan 28, 2016
Priority date	Jan 28, 2016
Publication date	Aug 3, 2017
Grant date	—

Abstract

The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam. The fir tree coupling may comprise a channel through the rounded base across a portion of the radius of curvature from the first side to the second side. The channel may comprise a sidewall having a sidewall step cut into a portion of the channel sidewall.

First claim

What is claimed is:

1 . A fir tree coupling comprising:
a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel the longitudinal axis and disposed on the first side of the load beam.

2 . The fir tree coupling of claim 1 , comprising a channel through the rounded base across a portion of the radius of curvature from the first side to the second side.

3 . The fir tree coupling of claim 2 , wherein the channel comprises a sidewall having a sidewall step cut into a portion of the channel sidewall.

4 . The fir tree coupling of claim 2 , wherein the channel comprises at least one of a concave sidewall having a concave curvature into the rounded base, a vertical sidewall extending perpendicular into the rounded base, or a wide channel wherein the wide channel extends across the length of the load beam between a first portion at a first end of the wide channel and a second portion at a second end of the wide channel.

5 . The fir tree coupling of claim 2 , wherein the channel comprises a tapered sidewall wherein the tapered sidewall extends at an angle into the rounded base.

6 . The fir tree coupling of claim 2 , wherein the channel is disposed at an angle to the longitudinal axis of the load beam.

7 . The fir tree coupling of claim 1 , wherein the tooth includes a bearing surface.

8 . The fir tree coupling of claim 1 , wherein the load beam comprises a top surface and a cooling passage passing through the load beam from the rounded base to the top surface.

9 . The fir tree coupling of claim 1 , wherein the load beam comprises at least one of nickel, nickel alloy, titanium, or titanium alloy.

10 . The fir tree coupling of claim 1 , wherein the load beam comprises a monocrystalline material.

11 . A turbine blade assembly for a gas turbine engine comprising:
a platform having a dorsal surface and a ventral surface; a turbine blade extending from the dorsal surface; a fir tree coupling extending from the ventral surface, the fir tree coupling comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam.

12 . The turbine blade assembly of claim 11 , wherein the fir tree coupling comprises a channel through the rounded base across a portion of the radius of curvature from the first side to the second side.

13 . The turbine blade assembly of claim 12 , wherein the channel comprises a sidewall having a sidewall step cut into a portion of the channel sidewall.

14 . The turbine blade assembly of claim 12 , wherein the channel comprises at least one of a concave sidewall having a concave curvature into the rounded base, a vertical sidewall extending perpendicular into the rounded base, or a wide channel wherein the wide channel extends across the length of the load beam between a first portion at a first end of the wide channel and a second portion at a second end of the wide channel.

15 . The turbine blade assembly of claim 12 , wherein, the channel comprises a tapered sidewall wherein the tapered sidewall extends at an angle into the rounded base.

16 . The turbine blade assembly of claim 12 , wherein the channel is disposed at an angle to the longitudinal axis of the load beam.

16 . The turbine blade assembly of claim 11 , wherein the fir tree coupling comprises a first cooling passage in fluid communication with a second a cooling passage within at least one of the platform or the airfoil.

17 . The turbine blade assembly of claim 11 , wherein the fir tree coupling comprises at least one of nickel, nickel alloy, titanium, or titanium alloy.

18 . The turbine blade assembly of claim 11 , wherein the fir tree coupling comprises a monocrystalline material.

19 . A method of manufacturing a fir tree coupling comprising:
forming a load beam having a longitudinal axis, a rounded base, a first side, a second side, and tooth running parallel to the longitudinal axis and disposed on the first side of the load beam, forming a radius of curvature on the rounded base from the first side to the second side.

20 . The method of claim 19 , further comprising forming a channel through the rounded base across a portion of the radius of curvature from the first side to the second side of the load beam.

Assignees

• United Technologies Corp

Inventors

• Thistle Charles
• Hassan Mohamed

Classifications

• F05D2300/175

  Superalloys · CPC title

• F05D2300/174

  Titanium alloys, e.g. TiAl · CPC title

• F01D5/323

  Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor · CPC title

• F05D2300/177

  Ni - Si alloys · CPC title

• F05D2240/24

  for turbines · CPC title