FIELD: engines and pumps.
SUBSTANCE: gas turbine engine comprises a high pressure compressor, its straightener is located on two resilient shells of a combustion chamber diffuser. The straightener is made together with the resilient shells or is connected with the resilient shells using soldering or welding. Length of the resilient shells is 0.3-3.5 Lca, where Lca is axial width of blades of the compressor straightener. Bottom shell is secured with flange of a labyrinth seal creating closed cavity between its and bottom resilient shell. The flange of the labyrinth seal can be made elastic and secured to the bottom shell by bolts and self-locking nuts.
EFFECT: invention improves reliability and service life of the gas turbine engine and its economical efficiency.
2 cl, 7 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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|
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