Sequential combustor arrangement with a mixer
US-2016215984-A1 · Jul 28, 2016 · US
Damper with bent neck for gas turbine
US10036327B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10036327-B2 |
| Application number | US-201414523040-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 24, 2014 |
| Priority date | Oct 28, 2013 |
| Publication date | Jul 31, 2018 |
| Grant date | Jul 31, 2018 |
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- Title
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- Abstract
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- Assignees and inventors
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Abstract
Official abstract text for this publication.
The invention relates to a damper for reducing the pulsations in a chamber of a gas turbine. The damper includes a resonator cavity and a neck in flow communication with the resonator cavity and the chamber. The neck includes a mouth to communicate with the chamber. The air flow inside the chamber flows across the mouth of the neck. The neck is so configured that the longitudinal axis of its mouth is angled 0-90° relative to the direction of the air flow inside the chamber. The damper of this invention may effectively alleviate the detrimental effect of the grazing flow and thus it enables the placement of the damper also at locations where strong grazing flows are present.
First claim
Opening claim text (preview).
The invention claimed is: 1. A damper for reducing the pulsations in a combustion chamber of a gas turbine where there is a combustion dynamic, the damper comprising: a resonator cavity; and a neck in flow communication with the resonator cavity and protruding into the combustion chamber, wherein the neck includes a mouth end inside the combustion chamber, wherein the damper is configured to produce air flow inside the combustion chamber across the mouth end of the neck, and wherein the neck inside the combustion chamber has a curved longitudinal axis such that the mouth end is angled from 0° to less than 90° relative to a direction of intended air flow inside the combustion chamber. 2. The damper according to claim 1 , wherein the neck is bent along the direction of intended air flow inside the combustion chamber. 3. The damper according to claim 2 , wherein the neck is bent with the longitudinal axis of the mouth end in alignment with the direction of intended air flow inside the combustion chamber.
Assignees
Inventors
Classifications
Noise absorbing means · CPC title
- F23R3/002Primary
Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title
by Helmholtz resonators · CPC title
- F02C7/24Primary
Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title
Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators · CPC title
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- What does patent US10036327B2 cover?
- The invention relates to a damper for reducing the pulsations in a chamber of a gas turbine. The damper includes a resonator cavity and a neck in flow communication with the resonator cavity and the chamber. The neck includes a mouth to communicate with the chamber. The air flow inside the chamber flows across the mouth of the neck. The neck is so configured that the longitudinal axis of its mo…
- Who is the assignee on this patent?
- Ansaldo Energia Switzerland AG
- What technology area does this patent fall under?
- Primary CPC classification F23R3/002. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jul 31 2018 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 1 related publication on this page (citations in our corpus or others sharing the same primary CPC).