FIELD: turbine engineering. SUBSTANCE: stator 2 consists of three housing 9,10 and 11 each of which encloses two stages of nozzle assemblies. Butts between outer rings 12, 17 and 21 are arranged downstream of nozzle blades 14 and 19 of each odd stage of the turbine. The even stages of the nozzle blades and split rings are connected with the outer ring or made in block with it. Insert 20 of the split rings of odd stages 1 and 3 is provided with face projections which engage radial grooves of the outer ring. The outer shelf of the nozzle blades of the odd stages are provided with radial grooves which engage the face projections of the outer ring. EFFECT: improved design. 4 dwg
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Year |
Author |
Number |
| GAS-TURBINE ENGINE |
1994 |
- Ivanov N.A.
- Kuznetsov V.A.
- Chernjaev I.A.
- Fadeev S.I.
|
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|
RU2006594C1 |
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|
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2016 |
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|
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| STATOR FOR AXIAL COMPRESSOR OF GAS-TURBINE ENGINE |
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- Kuznetsov V.A.
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|
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RU2630920C1 |
