Turbine rotor blade of a gas turbine and method for cooling a blade tip of a turbine rotor blade of a gas turbine
US-2015159488-A1 · Jun 11, 2015 · US
Turbine blade with tip overhang along suction side
US10641107B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10641107-B2 |
| Application number | US-201314062230-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 24, 2013 |
| Priority date | Oct 26, 2012 |
| Publication date | May 5, 2020 |
| Grant date | May 5, 2020 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A turbine blade has a root portion, a platform and an aerofoil, the aerofoil is mounted on the platform and is formed by a pressure side wall and a suction side wall and has an outer surface, the pressure side wall and the suction side wall meet at a leading edge and a trailing edge, the aerofoil has an axial chord length, the suction side wall defines part of the radially outward surface of the aerofoil, the suction side wall defines an overhang, the overhang has a maximum overhang length that is between 5% and 20% of the axial chord length of the blade and is located between 5% and 50% of the suction surface length from the leading edge.
First claim
Opening claim text (preview).
The invention claimed is: 1. A turbine blade comprising a root portion, a platform and an aerofoil, wherein: the aerofoil is mounted on the platform and is formed by a pressure side wall and a suction side wall and has an outer surface, the pressure side wall and the suction side wall meet at a leading edge and a trailing edge, the aerofoil has an aerofoil tip and an axial chord length, the suction side wall defines an overhang at the aerofoil tip, the overhang has a maximum overhang length that is between 5% and 20% of the axial chord length of the blade and is located between 15% and 40% of the suction surface length from the leading edge, and the overhang reduces in overhang length from the maximum overhang length towards the trailing edge until the overhang length reaches zero at a position between 50% and 100% of the suction surface length from the leading edge. 2. The turbine blade as claimed in claim 1 , wherein the overhang extends radially along the aerofoil a distance between 5% and 25% of the axial chord length from a radially outer surface of the aerofoil tip. 3. The turbine blade as claimed in claim 1 , wherein the overhang extends radially along the aerofoil a distance between 10% and 20% of the axial chord length from a radially outer surface of the aerofoil tip. 4. The turbine blade as claimed in claim 1 , wherein the maximum overhang length is between 10% and 15% of the axial chord length of the blade. 5. The turbine blade as claimed in claim 1 , wherein the overhang reduces in overhang length from the maximum overhang length towards the leading edge and towards the trailing edge. 6. A rotor stage of a turbine comprising: a rotational axis; shroud; the turbine blade as claimed in claim 1 radially inward of the shroud; and a clearance gap which is defined from a radially outward surface of the aerofoil tip to the shroud.
Assignees
Inventors
Classifications
- F01D5/20Primary
Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title
for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title
related to the tip of a rotor blade · CPC title
Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title
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Frequently asked questions
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- What does patent US10641107B2 cover?
- A turbine blade has a root portion, a platform and an aerofoil, the aerofoil is mounted on the platform and is formed by a pressure side wall and a suction side wall and has an outer surface, the pressure side wall and the suction side wall meet at a leading edge and a trailing edge, the aerofoil has an axial chord length, the suction side wall defines part of the radially outward surface of th…
- Who is the assignee on this patent?
- Rolls Royce Plc, Rolls Royce Deutschland Ltd & Co Kg
- What technology area does this patent fall under?
- Primary CPC classification F01D5/20. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue May 05 2020 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 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).