FIELD: engines and pumps.
SUBSTANCE: double-flow gas turbine engine compressor platform with primary and secondary flows, which restricts some part of nose part surface around which primary flow circulates, includes blades installed on it and made in radial outward direction starting from the platform. Between two adjacent blades there is projection projecting to the space between two blades, which is meant for creation of compression of primary air flow and located in the downstream zone between blades, which occupies 30% or 40% of that space. Projection is located close to rear edges of blades in primary flow circulation direction. One more invention of the group refers to gas turbine engine compressor containing the blades installed on the above platform. The other invention refers to gas turbine engine equipped with the above compressor.
EFFECT: inventions allow improving the compression efficiency of primary air flow with gas turbine engine compressor.
9 cl, 7 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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|
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|
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|
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|
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|
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|
RU2406879C2 |
| GAS TURBINE ENGINE COMPRESSOR AIR BLEEDER | 2008 |
|
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| CONTROLLED CONVERGENCE COMPRESSOR FLOWPATH FOR GAS TURBINE ENGINE | 2014 |
|
RU2673977C2 |
| GAS TURBINE ENGINE | 2012 |
|
RU2687861C2 |
