Turbine vane with coupon having corrugated surface(s)
US-2018023403-A1 · Jan 25, 2018 · US
Gas turbine blade with corrugated tip wall
US10260352B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10260352-B2 |
| Application number | US-201615139379-A |
| Country | US |
| Kind code | B2 |
| Filing date | Apr 27, 2016 |
| Priority date | Aug 1, 2013 |
| Publication date | Apr 16, 2019 |
| Grant date | Apr 16, 2019 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A gas turbine engine blade ( 10 ), including a base portion ( 12 ) having a cast wall, and a tip portion ( 14 ) attached to the base portion and having a wall ( 60 ) formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness. Openings ( 80 ) defining the wall corrugations may be semi-circular, rectangular, trapezoidal, or elliptical in cross-sectional shape. The resulting blade has lower tip mass while retaining adequate mechanical properties. The tip portion may be formed to have a directionally solidified grain structure on a base portion having an equiaxed grain structure.
First claim
Opening claim text (preview).
The invention claimed is: 1. A method of manufacturing a gas turbine engine blade, the method comprising forming a tip portion of the blade on a cast base portion of the blade by an additive manufacturing process, forming the tip portion to comprise a corrugated wall by the additive manufacturing process, wherein the corrugated wall comprises an inner panel, an outer panel, and integral connections there between, and forming the inner panel and the outer panel such that each comprises a cross-sectional thickness that is not greater than 0.5 millimeter in at least one respective location; and forming the corrugated wall to comprise a plurality of openings having semi-circular shapes when viewed in cross-section and disposed in a direction from a leading edge of the corrugated wall to a trailing edge of the corrugated wall along a length of the wall, adjacent semi-circular shapes having alternate orientations. 2. The method of claim 1 , wherein the cast base portion comprises a conventionally cast equiaxed grain structure, and further comprising forming the tip portion to comprise a directionally solidified grain structure. 3. The method of claim 1 , further comprising forming the tip portion to comprise a cross-sectional wall thickness that is different at two locations along a wall of the blade. 4. The method of claim 1 , further comprising forming the tip portion to comprise a corrugated structural rib by the additive manufacturing process. 5. The method of claim 1 , further comprising forming the tip portion such that a radial length of the tip portion is 5-40% of a total radial length of the blade.
Assignees
Inventors
Classifications
Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title
Operations & Transport · mapped topic
turbine or like blades from several pieces · CPC title
Processes of additive manufacturing · CPC title
trapezoidal · CPC title
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Frequently asked questions
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- What does patent US10260352B2 cover?
- A gas turbine engine blade ( 10 ), including a base portion ( 12 ) having a cast wall, and a tip portion ( 14 ) attached to the base portion and having a wall ( 60 ) formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness. Openings ( 80 ) defining the wall corrugati…
- Who is the assignee on this patent?
- Siemens Energy Inc
- What technology area does this patent fall under?
- Primary CPC classification F01D5/147. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Apr 16 2019 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 6 related publications on this page (citations in our corpus or others sharing the same primary CPC).