Systems and methods for variable microchannel combustor liner cooling
US-11859818-B2 · Jan 2, 2024 · US
Combustor turbine interface for a gas turbine engine
US9650903B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9650903-B2 |
| Application number | US-54969309-A |
| Country | US |
| Kind code | B2 |
| Filing date | Aug 28, 2009 |
| Priority date | Aug 28, 2009 |
| Publication date | May 16, 2017 |
| Grant date | May 16, 2017 |
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- Title
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Abstract
Official abstract text for this publication.
A turbine vane downstream of a combustor section includes an arcuate outer vane platform defined about an axis, the arcuate outer vane platform includes a segment of the arcuate outer vane platform along the axis which follows an outer combustor liner panel structure and an arcuate inner vane platform defined about the axis, the arcuate inner vane platform includes a segment of the arcuate inner vane platform along the axis which follows an inner combustor liner panel structure.
First claim
Opening claim text (preview).
What is claimed is: 1. A turbine vane downstream of a combustor section comprising: an arcuate outer vane platform defined about an axis, said arcuate outer vane platform includes a segment of said arcuate outer vane platform along said axis which follows an outer combustor liner panel structure; an arcuate inner vane platform defined about said axis, said arcuate inner vane platform includes a segment of said arcuate inner vane platform along said axis which follows an inner combustor liner panel structure; a vane which extends in a radial direction between said arcuate outer vane platform and said arcuate inner vane platform, said vane defines a leading edge which is set back from a forward most edge of said arcuate outer vane platform and said arcuate inner vane platform; and said segment of said arcuate outer vane platform and said segment of said arcuate inner vane platform follows a respective contour of the outer combustor liner panel structure and the inner combustor liner panel structure. 2. A gas turbine engine comprising: a combustor section which includes an outer combustor liner panel structure and an inner combustor liner panel structure defined about an axis; a turbine section downstream of said combustor section, said turbine section includes an arcuate outer vane platform and an arcuate inner vane platform defined about said axis, said arcuate outer vane platform includes a segment along said axis which follows said outer combustor liner panel structure and said arcuate inner vane platform includes a segment which follows said inner combustor liner panel structure to define a smooth flow path from said combustor section into said turbine section; a vane which extends in a radial direction between said arcuate outer vane platform and said arcuate inner vane platform, said vane defines a leading edge which is set back from a forward most edge of said arcuate outer vane platform and said arcuate inner vane platform; and said segment of said arcuate outer vane platform and said segment of said arcuate inner vane platform follows a respective step-less contour of said outer combustor liner panel structure and said inner combustor liner panel structure.
Assignees
Inventors
Classifications
Platforms for stationary or moving blades · CPC title
- F01D9/023Primary
Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title
using blades (F01D5/148 takes precedence) · CPC title
circular · CPC title
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Frequently asked questions
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- What does patent US9650903B2 cover?
- A turbine vane downstream of a combustor section includes an arcuate outer vane platform defined about an axis, the arcuate outer vane platform includes a segment of the arcuate outer vane platform along the axis which follows an outer combustor liner panel structure and an arcuate inner vane platform defined about the axis, the arcuate inner vane platform includes a segment of the arcuate inne…
- Who is the assignee on this patent?
- Hoke James B, Kirsopp Philip J, United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F01D9/023. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue May 16 2017 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).