Gas turbine cooling systems and methods
US-2017044909-A1 · Feb 16, 2017 · US
Pre-swirler adjustability in gas turbine engine
US12173609B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-12173609-B2 |
| Application number | US-202017597572-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jun 4, 2020 |
| Priority date | Jul 25, 2019 |
| Publication date | Dec 24, 2024 |
| Grant date | Dec 24, 2024 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A gas turbine engine having a pre-swirler adjustability is presented. The pre-swirler includes a pre-swirler insert installed in a component enclosed by a cover. The component includes an inner compressor exit diffusor enclosed by an outer casing or a shaft cover enclosed by the inner compressor exit diffusor. The pre-swirler is adjustable by replacing the pre-swirler insert. An access port including an access window is arranged on the cover. The access port gives access to the pre-swirler insert for replacement through the access window. The access window includes a manhole or combustor assembly installation hole on the outer casing, or a cutout on the inner compressor exit diffusor. The access port allows adjusting the pre-swirler by replacing the pre-swirler insert installed in the component without lifting the cover enclosing the component.
First claim
Opening claim text (preview).
What is claimed is: 1. A method for adjusting a pre-swirler arranged on a component of a gas turbine engine, wherein the pre-swirler comprises a pre-swirler insert installed in the component, wherein the pre-swirler insert is configured to be replaceable for adjustment, the method comprising: arranging an access port including an access window on a cover enclosing the component to give access to the pre-swirler insert installed in the component; and replacing the pre-swirler insert through the access window, wherein the cover comprises an inner compressor exit diffusor, wherein the component comprises a shaft cover, and wherein the access window is arranged by cutting a cutout on the inner compressor exit diffusor, further comprising turning the shaft cover using a clocking tool passing through the access window on the inner compressor exit diffusor for accessing a plurality of pre-swirler inserts through the access window. 2. The method as claimed in claim 1 , further comprising arranging a plurality of access ports on a circumference of the inner compressor exit diffusor for accessing a plurality of pre-swirler inserts respectively. 3. The method as claimed in claim 1 , further comprising replacing a torque pin installed in the inner compressor exit diffusor with a ball pin prior to turning the shaft cover.
Assignees
Inventors
Classifications
Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title
in a closed cavity · CPC title
cooling fluid circulating inside the rotor · CPC title
the fluid circulating at the periphery of a multistage rotor, e.g. of drum type · CPC title
on the side of the rotor disc · CPC title
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- What does patent US12173609B2 cover?
- A gas turbine engine having a pre-swirler adjustability is presented. The pre-swirler includes a pre-swirler insert installed in a component enclosed by a cover. The component includes an inner compressor exit diffusor enclosed by an outer casing or a shaft cover enclosed by the inner compressor exit diffusor. The pre-swirler is adjustable by replacing the pre-swirler insert. An access port inc…
- Who is the assignee on this patent?
- Siemens Energy Global Gmbh & Co Kg
- What technology area does this patent fall under?
- Primary CPC classification F01D25/243. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Dec 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 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).