Fatigue strength and life of compressor blades for marine gas turbine engines

1999 ◽  
Vol 31 (1) ◽  
pp. 18-27 ◽  
Author(s):  
V. T. Troshchenko ◽  
A. V. Prokopenko
Keyword(s):  
Fatigue Strength ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Compressor Blades

REMOVAL OF HARDENING COATINGS BASED ON TITANIUM NITRIDE AND ZIRCONIUM NITRIDE FROM THE SURFACE OF PARTS MADE OF TITANIUM ALLOYS

2020 ◽  
pp. 113-121
Author(s):  
D.A. Dobrynin ◽  
◽  
I.V. Iatsyuk ◽  
O.N. Doronin ◽  
◽  
...  
Keyword(s):  
Titanium Nitride ◽  
Titanium Alloys ◽  
Gas Turbine ◽  
Zirconium Nitride ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Compressor Blades ◽  
Hardening Coatings ◽  
Electrochemical Removal

Рrovides an overview of the methods of chemical and electrochemical removal of hardening coatings based on titanium nitride (TiN) and zirconium nitride (ZrN) from the surface of parts made of various materials that can be used to remove defective and waste coatings from the surface of compressor blades and other parts of gas turbine engines (GTE) from titanium alloys. The main disadvantages of the described methods are shown in relation to the removal of hardening coatings from the surface of compressor blades and other GTE parts made of titanium alloys. Taking into account the shortcomings of the available methods, FSUE «VIAM» has developed effective methods for chemical removal of hardening coatings based on titanium nitride and zirconium nitride from the surface of parts made of titanium alloys, and recommendations are given for controlling the completeness of removal of coatings.

Techniques and Methods to Improve the Dynamic Strength of Gas Turbine Engines Compressor Rotor Wheels

2014 ◽  
Author(s):  
Daria Kolmakova ◽  
Grigorii Popov ◽  
Aleksandr Shklovets ◽  
Aleksandr Ermakov
Keyword(s):  
Gas Turbine ◽  
Calculation Method ◽  
Gas Flow ◽  
Dynamic Strength ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Cfd Model ◽  
Compressor Blades ◽  
Compressor Rotor ◽  
Pressure Compressor

The approaches to reducing the alternating stresses in the compressor blades, arising at a resonance, are discussed in paper. Maximum alternating stresses in blades of the fifth stage of intermediate pressure compressor (IPC, that operating under the gas flow circumferential variation conditions, are defined on the basis of the forced blade oscillations calculation method. Parametric CFD-model which allows to introduce different stagger angles and circumferentially alternating blade pitch at the guide vanes of IPC fifth stage was created to reduce the stresses. The flow circumferential variation was reduced by changing these parameters and as a consequence the resonant stresses were decreased by more than 2.5 times.

scholarly journals Using Solid-State Joining in Gas Turbine Engines

1972 ◽  
Author(s):  
D. C. Martin ◽  
F. R. Miller
Keyword(s):  
Solid State ◽  
Gas Turbine ◽  
Engine Performance ◽  
Turbine Engines ◽  
Dissimilar Metals ◽  
Gas Turbine Engines ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Solid State Bonding ◽  
Solid State Joining

The ability to fabricate materials and components needed to improve gas-turbine engine performance depends on an ability to achieve reliable joints. Solid-state joining provides this ability. Diffusion bonding of compressor blades, friction welding of engine rotors, and solid-state bonding of turbine shafts by coextrusion of dissimilar metals are discussed as examples of applications of solid-state bonding. Parts made by these techniques have successfully completed engine tests.

Sign in / Sign up

Export Citation Format

Share Document