Turbine with a shroud ring around rotor blades and method of limiting leakage of working fluid in a turbine
US-2024280031-A1 · Aug 22, 2024 · US
Gas turbine engines with abradable turbine seal assemblies
US9068469B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9068469-B2 |
| Application number | US-201113224035-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 1, 2011 |
| Priority date | Sep 1, 2011 |
| Publication date | Jun 30, 2015 |
| Grant date | Jun 30, 2015 |
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- Title
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Abstract
Official abstract text for this publication.
A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.
First claim
Opening claim text (preview).
What is claimed is: 1. A turbine section of a gas turbine engine, comprising: a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow; a rotor assembly including a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path; a first stator assembly positioned adjacent to the rotor assembly on a downs…
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Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Cross-Sectional Technologies · mapped topic
Mechanical Engineering · mapped topic
- F01D11/122Primary
Mechanical Engineering · mapped topic
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Frequently asked questions
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- What does patent US9068469B2 cover?
- A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainst…
- Who is the assignee on this patent?
- Tucker Bradley Reed, Smoke Jason, Morris Mark C, and 1 more
- What technology area does this patent fall under?
- Primary CPC classification F01D11/122. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jun 30 2015 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 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).