Low noise turbine for geared turbofan engine
US12123432B2 · kind B2 · utility
Assignees
Inventors
Key dates
| Filing date | May 25, 2023 |
| Grant date | Oct 22, 2024 |
| Priority date | — |
| Expiry date | May 25, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/333
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An aircraft system includes, among other things, an aircraft and a gas turbine engine coupled to the aircraft. The gas turbine engine includes a propulsor section including a propulsor, a compressor section, a turbine section including a first turbine and a second turbine, and a gear reduction between the propulsor and the second turbine. The second turbine includes a number of turbine blades in each of a plurality of rows of the second turbine. The second turbine blades operating at least some of the time at a rotational speed. The number of blades and the rotational speed being such that the following formula holds true for a majority of the blade rows of the second turbine: 5500 Hz≤(number of blades×speed)/60 sec≤10000 Hz. The gas turbine engine is rated to produce 15,000 pounds of thrust or more.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.