Gas turbine combustor
US-2020300471-A1 · Sep 24, 2020 · US
Gas turbine combustor and gas turbine
US12098847B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-12098847-B2 |
| Application number | US-202118027182-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 5, 2021 |
| Priority date | Oct 7, 2020 |
| Publication date | Sep 24, 2024 |
| Grant date | Sep 24, 2024 |
How to read this patent
A practical reading order for non-experts. Skip the full description unless you need deep technical detail.
- Title
What the patent document calls the invention.
- Abstract
A short plain-language summary of the technical disclosure.
- Assignees and inventors
Who owns or filed the patent and who is credited as inventor.
- Key dates
Filing, priority, publication, and grant dates set the timeline.
- First independent claim
The legal scope of protection — read this for what is actually claimed.
- CPC / IPC classifications
Technology tags used to group this patent with similar filings.
- Citations and related patents
Prior art links and similar publications in this corpus.
Abstract
Official abstract text for this publication.
A gas turbine combustor according to at least one embodiment is a gas turbine combustor that includes: a tubular member; a plurality of premixing tubes circumferentially arranged on an inner side of the tubular member, each of the plurality of premixing tubes forming an outlet portion of a premixing passage; and a base plate for supporting the plurality of premixing tubes. The base plate has: a plurality of through holes disposed corresponding to the plurality of premixing tubes, respectively, and allowing the premixing passage to pass through the base plate; and a plurality of oblique holes extending obliquely with respect to an axial direction of the gas turbine combustor in a region different from a region where the through holes are disposed.
First claim
Opening claim text (preview).
The invention claimed is: 1. A gas turbine combustor, comprising: a tubular member; a plurality of premixing tubes circumferentially arranged on an inner side of the tubular member, each of the plurality of premixing tubes forming an outlet portion of a premixing passage; and a base plate for supporting the plurality of premixing tubes, wherein the base plate has: a plurality of through holes disposed corresponding to the plurality of premixing tubes, respectively, and allowing the premixing passage to pass through the base plate; and a plurality of oblique holes extending obliquely with respect to an axial direction of the gas turbine combustor in a region different from a region where the through holes are disposed, wherein the plurality of oblique holes includes first holes, each first hole being positioned radially outward of a central position of a corresponding one of the plurality of through holes, and each first hole extending obliquely with respect to the axial direction and radially outward from an upstream end toward a downstream end, and wherein each of the first holes extends obliquely with respect to the axial direction and when viewed from outside in a radial direction of the gas turbine combustor toward a central position of an outlet opening of a corresponding one of the premixing tubes among the plurality of premixing tubes from the upstream end toward the downstream end. 2. The gas turbine combustor according to claim 1 , wherein the plurality of oblique holes include second holes each of which is positioned radially inward of a central position of a corresponding one of the plurality of through holes, and extends obliquely with respect to the axial direction and radially inward from an upstream end toward a downstream end. 3. The gas turbine combustor according to claim 2 , wherein each of the second holes extends obliquely with respect to the axial direction and when viewed from the outside in a radial direction of the gas turbine combustor toward a central position of an outlet opening of a corresponding one of the premixing tubes among the plurality of premixing tubes from the upstream end toward the downstream end. 4. The gas turbine combustor according to claim 1 , wherein at least some oblique holes of the plurality of oblique holes are disposed in a region of the base plate overlapping outlet openings of the premixing tubes, when viewed from a downstream side. 5. A gas turbine, comprising: the gas turbine combustor according to claim 1 .
Assignees
Inventors
Classifications
Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title
Combustors or associated equipment · CPC title
Fuel supply systems · CPC title
in gas turbines · CPC title
- F23R3/286Primary
having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title
Patent family
Related publications grouped by family.
External sources
Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US12098847B2 cover?
- A gas turbine combustor according to at least one embodiment is a gas turbine combustor that includes: a tubular member; a plurality of premixing tubes circumferentially arranged on an inner side of the tubular member, each of the plurality of premixing tubes forming an outlet portion of a premixing passage; and a base plate for supporting the plurality of premixing tubes. The base plate has: a…
- Who is the assignee on this patent?
- Mitsubishi Heavy Ind Ltd
- What technology area does this patent fall under?
- Primary CPC classification F23R3/286. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Sep 24 2024 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).