Back to results
US 2019/0376528 A1Published application
Modal noise reduction for gas turbine engine
AssigneeUnited Technologies Corporation
InventorDavid A. Topol
Life of this patent
Estimating the term…
Abstract
An exemplary section of a gas turbine engine according to this disclosure includes, among other things, a first array of airfoils including a first number of airfoils, and a second array of airfoils downstream of the first array of airfoils. The second array includes a second number of airfoils. The second number of airfoils is at least 1.19 times the first number of airfoils thereby providing a predetermined modal.
Claims20
A section of a gas turbine engine, comprising:
- a first array of airfoils, the first array including a first number of airfoils;
- and
- a second array of airfoils downstream of the first array of airfoils, the second array including a second number of airfoils, wherein the second number of airfoils is at least 1.19 times the first number of airfoils thereby providing a predetermined modal.
A gas turbine engine, comprising:
- a low pressure compressor including a first array of airfoils and a second array of airfoils downstream of the first array, the first array including a first number of airfoils and the second array including a second number of airfoils, wherein the second number of airfoils is at least 1.19 times the first number of airfoils thereby providing a predetermined modal.
A method, comprising:
- controlling an interaction between a first array of airfoils and a second arrays of airfoils during operation of a gas turbine engine by providing a number of airfoils in the second array that is at least 1.19 times the number of airfoils in the first array, wherein the second array of airfoils is downstream of the first array of airfoils.
Dependencies are inferred from the claim text.