Rolling tool device
US-2015367459-A1 · Dec 24, 2015 · US
Gas turbine engine rotor balancing
US9511457B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9511457-B2 |
| Application number | US-201213369684-A |
| Country | US |
| Kind code | B2 |
| Filing date | Feb 9, 2012 |
| Priority date | Feb 9, 2012 |
| Publication date | Dec 6, 2016 |
| Grant date | Dec 6, 2016 |
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- Title
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Abstract
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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 method of balancing a gas turbine engine rotor, the method comprising: a) obtaining a rotor disc with a circumferential array of tabs projecting from a peripheral rim of the disc and with stress shielding scallops between the tabs, wherein the tabs are created by machining the stress shielding scallops in a radially inner surface of the peripheral rim of the disc, the tabs projecting radially inwardly from the peripheral rim, the tabs having a predetermined initial weight; b) measuring a rotational imbalance of the rotor; and then c) correcting at least a part of the measured imbalance by removing material from at least one of the tabs to reduce the predetermined initial weight thereof to a reduced weight. 2. The method defined in claim 1 , wherein a) comprises manufacturing the rotor disc initially with the stress shielding scallops and the tabs in the peripheral rim of the rotor disc. 3. The method defined in claim 1 , wherein c) comprises machining off at least a portion of said at least one of said tabs. 4. The method defined in claim 3 , wherein the tabs are substantially aligned with a trailing edge of the blades. 5. The method defined in claim 1 , wherein c) comprises performing a straight cut in the at least one of the tabs. 6. The method defined in claim 1 , wherein a circumferential array of blades extend radially outwardly from a radially outer surface of the peripheral rim of the rotor disc, and wherein a) comprises providing the tabs at circumferential locations generally corresponding to the blades.
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Frequently asked questions
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- What does patent US9511457B2 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?
- Stone Paul, Pratt & Whitney Canada
- What technology area does this patent fall under?
- Primary CPC classification B23P15/02. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Dec 06 2016 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).