Computationally balancing a rotating structure
US-2024230448-A1 · Jul 11, 2024 · US
Gas turbine engine rotor balancing
US10598018B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10598018-B2 |
| Application number | US-201615341331-A |
| Country | US |
| Kind code | B2 |
| Filing date | Nov 2, 2016 |
| Priority date | Feb 9, 2012 |
| Publication date | Mar 24, 2020 |
| Grant date | Mar 24, 2020 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.
First claim
Opening claim text (preview).
What is claimed is: 1. A manufacturing method for a gas turbine engine rotor having a disc rotatable about an axis, the disc having a peripheral rim from which circumferentially spaced-apart blades project radially outwardly, the manufacturing method comprising a) forming a circumferential array of stress shielding scallops in a radially inner surface of the peripheral rim of the disc, the stress shielding scallops forming a circumferential array of initial balance tabs projecting radially from said radially inner surface of the peripheral rim of the disc, including machining a fillet in the radially inner surface of the peripheral rim between each of the initial balance tabs and neighboring ones of the stress shielding scallops; b) measuring a rotor imbalance about the axis; and c) substantially correcting the measured imbalance by removing material from at least a selected one of said initial balance tabs, wherein prior or after step c) the method further comprises: performing a surface inspection and a surface treatment operation on said rotor including on said stress shielding scallops thereof. 2. The manufacturing method defined in claim 1 , wherein the surface inspection and the surface treatment operation are performed prior to step c). 3. The manufacturing method defined in claim 1 , wherein the stress shielding scallops are defined in an aft end portion of the peripheral rim.
Assignees
Inventors
Classifications
in gas turbines · CPC title
Blade making · CPC title
Load balancing · CPC title
- F01D5/027Primary
Arrangements for balancing (for balancing rotating bodies in general F16F15/32; for compensating imbalance G01M1/36) · CPC title
by removing material · CPC title
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Frequently asked questions
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- What does patent US10598018B2 cover?
- A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.
- Who is the assignee on this patent?
- Pratt & Whitney Canada
- What technology area does this patent fall under?
- Primary CPC classification F01D5/027. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Mar 24 2020 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).