Title:
TURBINE COOLING FOR GAS TURBINE ENGINES
Document Type and Number:
WIPO Patent Application WO/2019/066750
Kind Code:
A3
Abstract:
Instead of cooling the turbine disk blades of the gas turbine engines using a very stressful and expensive method of stealing from the compressor air at a temperature of 650 degrees Celsius, it is possible to provide a much effective cooling by using fan stages (1) located on a second shaft (2) added to the entry point of the engine main shaft (5), which allows the cooling of HPT (8) and LPT (9) disks and blades (12,13) with air so much cooler than the air provided in the conventional method.
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Inventors:
UYANIK TALAT (TR)
ERIM MEHMET (TR)
ERIM MEHMET (TR)
Application Number:
PCT/TR2018/050235
Publication Date:
January 16, 2020
Filing Date:
May 16, 2018
Export Citation:
Assignee:
UYANIK TALAT (TR)
ERIM MEHMET (TR)
ERIM MEHMET (TR)
International Classes:
F01D5/08; F01D5/18
Foreign References:
| EP2246525A1 | 2010-11-03 | |||
| GB913167A | 1962-12-19 | |||
| US2865598A | 1958-12-23 |
Attorney, Agent or Firm:
REHBER MARKA PATENT DANISMANLIK HIZMETLERI LTD STI (TR)
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