Aerodynamic designing method of the central section of small size gas turbine engines
US11423198B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 3, 2020 |
| Grant date | Aug 23, 2022 |
| Priority date | — |
| Expiry date | Nov 10, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T90/00
- WIPO fieldComputer technology
- WIPO sectorElectrical engineering
Abstract
This invention proposes the aerodynamic designing method for the central section of small size gas turbine engine type and it includes the following 8 steps: 1st step: checking to confirm if compressor outlet air meets demand specified by the central section; 2nd step: estimating the inner casing diameter based on practical experience; 3rd step: estimating the outer casing diameter; 4th step: estimating the combustor dome height and combustor length; 4th step: estimating the combustor dome height and combustor length; 5th step: estimating the combustor inner and outer liner diameters; 6th step: estimating the exit inner and exit outer diameters of the pre-diffuser; 7th step: estimating the dump gap; 8th step: verifying rotordynamic properties to determine if the shaft diameter assumption starting in the 2nd step is good enough.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.