FIELD: machine building.
SUBSTANCE: in the gas turbine manufacturing method for the modified gas turbine 200 manufacturing, having a different cycle, based on the base gas turbine 100 containing base compressor 1, compressor 201 of modified gas turbine 200 is configured to add at least one additional stage 53i on the upstream side, than last stage 53h of basic compressor 1, and on the downstream side of the air bleed slot 72 from the air removal chamber 74 of the said basic compressor 1, wherein said compressor 201 is made on the basis of this design and said modified gas turbine 200 is made.
EFFECT: therefore, it is possible to manufacture gas turbine, which is capable of providing a margin for compressor surging taking into account fluctuations in fuel composition.
8 cl, 10 dwg
Title | Year | Author | Number |
---|---|---|---|
IMPROVED METHOD OF TURBINE COMPRESSOR CHARACTERISTICS | 2017 |
|
RU2741172C2 |
DEVICE FOR AERODYNAMIC SEALING OF CLEARANCE BETWEEN BUTT ENDS OF AXIAL-FLOW COMPRESSOR ROTOR BLADES AND TURBINE SHELL | 2004 |
|
RU2261372C1 |
TURBINE ENGINE (VERSIONS) | 2008 |
|
RU2397351C2 |
BLADE WITH NARROW MIDDLE PART | 2000 |
|
RU2219377C2 |
DEVICE FOR OPTIMISATION OF RADIAL CLEARANCES OF AIRCRAFT GAS TURBINE ENGINE MULTISTAGE AXIAL-FLOW COMPRESSOR | 2012 |
|
RU2506436C2 |
SURGE IN THE GAS COMPRESSOR PREDICTING METHOD | 2016 |
|
RU2678155C1 |
GAS-TURBINE ENGINE COMPRESSOR | 2009 |
|
RU2498117C2 |
ADJUSTMENT DEVICE OF GUIDE BLADES OF AXIAL COMPRESSOR, SYSTEM OF ROTATING GUIDE BLADES OF AXIAL COMPRESSOR, AND CONTROL METHOD OF GUIDE BLADES OF AXIAL COMPRESSOR | 2009 |
|
RU2509897C2 |
HIGH-PRESSURE MULTISTAGE COMPRESSOR OF GAS-TURBINE ENGINE | 2005 |
|
RU2317447C2 |
TURBO-MACHINE STAGE | 1998 |
|
RU2148732C1 |
Authors
Dates
2019-10-29—Published
2016-04-11—Filed