RU2533223C1 - Method for gas turbine blade processing - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: proposed process comprises simultaneous electrochemical forming of root profile and butt part and hardening. Hardening is executed by ion implantation at energy of 25 to 30 keV in amount of 1.6·10¹⁷ cm^-2 to 2·10¹⁷ cm^-2 at the rate of portion increase of 0.7·10¹⁵ s^-1 to 1·10¹⁵ s^-1. Ions Cr, V, Y, Yb, C, B, Zr, N, La, Ti or their combinations are use while said hardening by ion implementation is executed after electrochemical forming of root profile and butt part and hardening.

EFFECT: higher fatigue strength of gas turbine blades.

18 cl, 1 ex

Description

The invention relates to electrophysical and electrochemical processing methods, in particular to a method for dimensional and hardening treatment of GTE blades, mainly from chromium-containing stainless steel alloys, as well as titanium and titanium alloys, and can be used in turbomachinery in the treatment of working and guide vanes of steam turbines, blades gas pumping units and compressors of gas turbine engines, in order to ensure the necessary physical, mechanical and operational properties of parts of turbomachines.

The working blades of the compressor of a gas turbine engine (GTE) and gas turbine installation (GTU), as well as steam turbines during operation, are exposed to significant dynamic and static loads, as well as corrosion and erosion destruction. Based on the performance requirements, for the manufacture of gas turbine compressor blades, high-alloy chromium, chromomolybdenum (CrMo), chromomolybdenum-vanadium (CrMoV) and other medium and high alloy steels are used (for example, for steam turbine blades - steel grades 20X13 and 15X11MF, gas turbines - steel 20X13, EI 961). These steels are among the stainless steels with a Cr content of 11-14%, differing in the content of alloying elements: C, Mo, V. In addition, titanium alloys are used for the manufacture of gas turbine compressor blades, which, in comparison with technical titanium, have higher strength, including at high temperatures, while maintaining a sufficiently high ductility and corrosion resistance (for example, titanium alloys of the grades VT6, VT14, VT3-1, VT22, etc.).

However, turbine blades of these steels and alloys are highly sensitive to stress concentrators. Therefore, the defects formed in the manufacturing process of these parts are unacceptable, since they cause the occurrence of intense destruction processes. This causes problems when machining surfaces of turbomachine parts. In this regard, the development of methods for producing high-quality surfaces of turbomachine parts is a very urgent task.

The most promising methods for processing turbomachine blades are electrochemical methods of polishing surfaces [Griliches S.Ya. Electrochemical and chemical polishing: Theory and practice. Effect on the properties of metals. L., Mashinostroenie, 1987], while the methods of electrolyte-plasma polishing (EPP) of parts are of the greatest interest for the field under consideration [for example, Patent GDR (DD) No. 238074 (A1), cl. C25F 3/16, publ. 08/06/86., As well as the Patent of the Republic of Belarus No. 1132, cl. C25F 3/16, 1996, BI No. 3].

A known method of processing metal surfaces, including anode processing in an electrolyte [Patent RB No. 1132, class. C25F 3/16, 1996, BI No. 3], as well as a method for electrochemical processing [US Patent No. 5028304, class. B23H 3/08, C25F 3/16, C25F 5/00, publ. 07/02/91].

However, the known methods of electrochemical processing do not allow to obtain a high-quality surface layer of the material, providing enhanced performance characteristics of the part.

Closest to the claimed technical solution is a method of dimensional electrochemical processing [A.S. USSR No. 1478520, IPC B23H 5/06, Method for dimensional electrochemical processing of GTE blades. Publ. September 20, 2005]. The known method of dimensional electrochemical processing of GTE blades includes the electrochemical formation of a pen profile, electrochemical polishing and surface plastic deformation. Moreover, to increase the fatigue strength of the blades, bead peening is carried out before electrochemical polishing, and during the subsequent electrochemical polishing, part of the riveted layer is removed. However, the known method of combining dimensional and hardening treatment does not allow to obtain high operational characteristics of the blade, in particular its fatigue strength, since repeated electrochemical treatment after hardening reduces the quality of the surface layer of the part. At the same time used in the prototype [A.S. USSR No. 1478520] the method of hardening processing of a blade can be used only before polishing its surface.

The task to which the claimed invention is directed is to ensure, immediately after completion of the process of electrochemical processing of the surface of the blade, protective hardening treatment that does not impair the microgeometry of the surface and has the effect of doping the surface layer of the material of the part.

The technical result of the invention is to increase the fatigue strength of GTE blades.

The technical result is achieved by the fact that in the method of processing a GTE blade, including the simultaneous electrochemical formation of the profile of the pen and the glue section, hardening processing, in contrast to the prototype, hardening processing is carried out by ion implantation at an energy of 25 to 30 keV, with a dose of 1.6 · 10 ¹⁷ cm ^-2 to 2 · 10 ¹⁷ cm ^-2 , with a dose rate of 0.7 · 10 ¹⁵ s ^-1 to 1 · 10 ¹⁵ s ^-1 , ions of Cr, V, Y, Yb are used, C, B, Zr, N, La, Ti, or combinations thereof, the ion implantation hardening treatment being carried out after electrochemical f framing the profile of the pen and the nibble area.

The technical result is also achieved by the fact that in the method of processing a GTE blade, before ion implantation hardening treatment, either electrochemical polishing or electrolyte-plasma polishing is carried out, and before polishing, as process variants, shot peening is carried out, while the ratio of the diameter of the shot to the radius the outlet edge of the feather blade is selected within 0.3 ... 4, and after shot peening, during polishing, remove the surface layer with a thickness of 0.04 ... 0.3 of the depth of the riveted layer.

The technical result is also achieved by the fact that in the method of treating a GTE blade, after polishing, before hardening the ion implant treatment, shot peening is carried out with a flow of microspheres with a diameter of 10 ... 80 μm at a speed of 10 ... 30 m / s.

The technical result is also achieved by the fact that in the method of processing a GTE blade, ion implantation is carried out either in a pulsed mode or in a continuous mode, and after ion implantation hardening treatment, postimplantation annealing is carried out.

The technical result is also achieved by the fact that in the method of processing a GTE blade, GTE compressor blades are used as gas turbine engine parts from high alloy steels or titanium alloys, moreover, after the ion-implantation hardening treatment by the ion-plasma method, a coating is applied: either from superhard compounds of one of refractory metals of IV-VI groups of the Periodic system of elements (Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W) with N, C, B or Si, or a multilayer coating of alternating layers of Me and metal compounds with nitrogen - Me -N, Me-C carbon or carbon and nitrogen - Me-NC, where Me is Ti, Zr, TiZr, N is nitrogen, C is carbon.

The inventive method of processing a blade of a gas turbine engine is as follows. The machined blank of the blade is placed in the cavity of the cathode - an instrument having a shape corresponding to the shape of the manufactured blade, immersed in a bath with an aqueous solution of electrolyte, fed to the blank-anode potential and the part is processed to obtain the desired shape and size. After dimensional treatment with an electrochemical or electrolyte-plasma method, an ion-implantation protective-hardening treatment is performed and, if necessary, a protective coating is applied. Ion-implantation treatment and coating are carried out in one installation of a complex ion-implantation treatment and ion-plasma coating. For this, the obtained blade blanks are placed in the installation chamber, the necessary vacuum is created, ion cleaning is performed, then the ion-implant treatment, after which, if necessary, a protective coating is applied. After coating, without removing the workpiece from the vacuum installation, post-implantation annealing is performed. Then, after cooling the blanks of the blades, they are removed from the installation and quality control of the processing is performed. The described sequence of operations of ion implantation and protective coating can also be performed in separate installations: ion-implantation installation, ion-plasma installation for coating and a vacuum furnace.

The electrochemical dimensional processing of billets, depending on the type of alloy, is carried out at current densities from 30 A / dm ² to 100 A / dm ² .

Electrochemical polishing at current densities from 0.1 A / dm ² to 1.1 A / dm ² . Shot peening can be carried out before polishing. The use of shot peening before electrochemical polishing allows for additional hardening treatment and to remove some of the defects of the surface layer that arose during electrochemical dimensional processing. In this case, the ratio of the diameter of the fraction to the radius of the outlet edge of the feather blade is chosen in the range of 0.3 ... 4. The ratio between the diameter of the fraction and the radius of the output edge is selected from considerations of eliminating re-riveting thin sections of the scapula. With subsequent polishing of the surface of the workpiece, remove the surface layer with a thickness of 0.04 ... 0.3 depth of the riveted layer.

In order to carry out additional hardening treatment, as a variant of the method after polishing, before hardening ion implant treatment, shot peening can also be carried out with a flow of microspheres with a diameter of 10 ... 80 μm at a speed of 10 ... 30 m / s. This treatment allows you to reduce the number of defects that occur during electrochemical polishing, to increase the uniformity of the surface layer of the workpiece material.

Ion implantation can be performed either in pulsed mode or in continuous mode. In this case, ions of such elements as Cr, V, Y, Yb, C, B, Zr, N, La, Ti or their combinations are used as implantable ions, at energies from 25 to 30 keV, with a dose of 1.6 · 10 ¹⁷ cm ^-2 to 2 · 10 ¹⁷ cm ^-2 , with a dose rate from 0.7 · 10 ¹⁵ s ^-1 to 1 · 10 ¹⁵ s ^-1 . After ion-implantation hardening treatment, post-implantation annealing is carried out, the temperature of which and the exposure time depend on the alloy used for the manufacture of the blade, the selected type of ion, and the implantation dose.

If it is necessary to protect the surface of the part from the effects of destructive operating factors (for example, erosion, corrosion, etc.), after ion-implantation hardening treatment, the ion-plasma method is used to coat from superhard compounds of one of the refractory metals of groups IV-VI of the Periodic system of elements (Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W) with N, C, B, Si or a multilayer coating is applied from alternating layers of Me and metal compounds with nitrogen - Me-N, Me-C carbon or carbon and nitrogen - Me-NC, where Me - Ti, Zr, TiZr, and N - nitrogen, - carbon.

During electrolyte-plasma treatment (polishing), a positive voltage is applied to the workpiece, a negative voltage is applied to the electrolyte (anode treatment) or a negative voltage is applied to the product, and a positive voltage is applied to the electrolyte (cathode treatment), as a result of which a vapor-gas shell forms around the part and the occurrence of a discharge between the workpiece and the electrolyte. Processing is carried out in an electrolyte medium while maintaining a vapor-gas shell around a part. Under the action of electric voltage (electric potential between the part and the electrolyte), a discharge arises in the vapor-gas shell, which is an ionized electrolytic plasma, which ensures the flow of intensive chemical and electrochemical reactions between the treated part and the medium of the gas-vapor shell.

When a positive potential is applied to the part, during the course of these reactions, the surface of the part is anodized with the chemical etching of the formed oxide. Moreover, with anodic polarization, the vapor-gas layer consists of electrolyte vapors, anions, and gaseous oxygen. Since etching occurs mainly on microroughnesses, where a thin oxide layer is formed, and the anodizing processes continue, as a result of the combined action of these factors, the roughness of the treated surface decreases and, as a result, polishing of the latter occurs.

In the case of cathodic polarization, the vapor-gas shell around the part consists of electrolyte vapors, cations and hydrogen gas, therefore, along with the chemical interaction of cations with the material of the surface layer of the part, micro spark discharges occur in the vapor-gas shell, which leads to electroerosive and cavitation effects on the treated surface.

Example 1. The workpiece blank of a turbomachine blade made of chrome steel grade 20X13 was placed in the cavity of the cathode-instrument, immersed in a bath with an aqueous solution of electrolyte, and then applying positive voltage to the part and negative voltage to the electrolyte, we processed it. Billets were processed in an electrolyte medium based on an aqueous solution of ammonium sulfate with a concentration of 0.8 ... 3.4%. After dimensional processing, the parts were subjected to electrochemical polishing. At the initial microroughness height of 0.63 microns after the polishing process, it was 0.12 microns.

In addition, the processing of steels of grades 15X11MF, EI 961, EP - 718 (showing similar results) in electrolytes of the compositions, wt.%:

1. (NH ₄ ) ₂ SO ₄ - 5; Trilon B - 0.8.

2. containing sulfuric and phosphoric acid, a block copolymer of ethylene and propylene oxides and the sodium salt of sulfonated butyl oleate in the following ratio of components, wt.%

Sulfuric acid - 10-30

Orthophosphoric acid - 40-80

Block copolymer of ethylene oxide and propylene - 0.05-1.1

Sodium salt of sulfonated butyl oleate - 0.01-0.05

Water - The rest.

3. aqueous solutions of salts of inorganic acids of ammonium and alkali metals or salts of lower carboxylic acids, as well as solutions of free acids.

4. an electrolyte containing an ammonium salt of an inorganic acid, ammonium salts of lower carboxylic acids and organic or inorganic substances forming complex compounds with alloy metals.

5. aqueous solutions of sodium salts (3-22% solution of sodium hydrogencarbonate).

6. aqueous solutions of ammonium chloride, sodium chloride.

7. aqueous solutions of ammonium salts (ammonium citrate one- or two- or trisubstituted, or mixtures thereof in the following ratio of components, wt.%:

Ammonium citrate mono-, or two-, or trisubstituted, or mixtures thereof - 2-18,

Water - Else).

After the dimensional electrochemical processing, polishing and ion-implant treatment, samples of high alloy steels and nickel-based alloys 20X13, 15X11MF, EI961, EP866, and EP708 were coated on the samples by the proposed method.

Modes of sample processing and coating according to the proposed method.

Ion purification: argon ions at an energy of 6 keV - unsatisfactory result (N.R.); 8 keV - satisfactory result (U.R.); 10 keV (U.R.); 12 keV (N.R.); current density: 110 MkA / cm ² (N.R.); 130 MkA / cm ² (U.R.); 160 MkA / cm ² (U.R.); 180 MkA / cm ² (N.R.); ion cleaning time: 0.1 hours (N.R.); 0.3 hours (U.R.); 1.0 hours (U.R.); 1.5 hours (N.R.).

Ion implantation with Cr, V, Y, Yb, C, B, Zr, N, La, Ti ions and their combinations: energy - 20 keV - Unsatisfactory result (N.R.); 25 keV - Satisfactory Result (UR); 30 keV (U.R.); 40 keV (N.R.); dose - 1.2 · 10 ¹⁷ cm ^-2 (N.R.); 1.6 · 10 ¹⁷ cm ^-2 (U.R.); 2 · 10 ¹⁷ cm ^-2 (U.R.); 3 · 10 ¹⁷ cm ^-2 (N.R.); dose rate - 0.4 · 10 ¹⁵ s ^-1 (N.R.); 0.7 · 10 ¹⁵ s ^-1 (U.R.); 1 · 10 ¹⁵ s ^-1 (U.R.); 3 · 10 ¹⁵ s ^-1 (N.R.).

The creation of the required vacuum was carried out by a turbomolecular pump; created a vacuum from 10 ^-5 to 100 ^-7 mm Hg

After processing the parts, postimplantation annealing was performed in one vacuum volume of the installation in one technological cycle.

Ion implantation was performed both in pulsed and continuous modes. As parts from titanium alloys, the compressor blades of a gas turbine engine, the blades of a gas turbine plant and the blades of a steam turbine were used.

Before polishing, a shot peening was carried out, while the ratio of the diameter of the shot to the radius of the outlet edge of the feather blade was chosen in the range of 0.3 ... 4, (0.2 (N.R.); 0.3 (U.R.); 0, 8 (U.R.); 1.6 (U.R.); 2.4 (U.R.); 4.0 (U.R.); 4.6 (N.R.).

After shot peening, during polishing, the surface layer was removed with a thickness of 0.04 ... 0.3 of the depth of the riveted layer (0.02 (N.R.); 0.04 (U.R.); 0.08 (U.R. ); 0.16 (U.R.); 0.3 (U.R.); 0.35 (N.R.).

After polishing, before hardening by ion implant treatment, shot peening was carried out with a flow of microspheres with a diameter of 10 ... 80 μm (8 μm (N.R.); 10 μm (U.R.); 20 μm (U.R.); 40 microns (U.R.); 60 microns (U.R.); 80 microns (U.R.); 100 microns (N.R.)) at a speed of 10 ... 30 m / s (6 m / s (N.R.); 10 m / s (U.R.); 20 m / s (U.R.); 30 m / s (U.R.); 40 m / s (N.R.) .

The coatings were applied by the ion-plasma method from superhard compounds of one of the refractory metals of groups IV-VI of the Periodic Table of the Elements (Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W) with N, C, B or Si. The following systems were used to obtain coatings: Ti-N, Zr-N, Hf-N, VN, Nb-N, Ta-N, Cr-N, Mo-N, WN, Ti-C, Zr-C, Hf-C , VC, Nb-C, Ta-C, Cr-C, Mo-C, WC, Ti-C, Zr-Si, Hf-Si, V-Si, Nb-Si, Ta-Si, Cr-Si, Mo -Si, W-Si. In addition, a multilayer coating was applied from alternating layers of Me and metal compounds with nitrogen - Me-N, carbon Me-C or carbon and nitrogen - Me-NC, where Me - Ti, Zr, TiZr, a N - nitrogen, C-carbon .

The thickness of the metal layer in the pair: 40 nm (N.R.); 50 nm (U.R.); 60 nm (U.R.); 80 nm (N.R.). The thickness of the layer of metal compounds with nitrogen in pairs: 200 nm (N.R.); 300 nm (U.R.); 400 nm (U.R.); 500 nm (N.R.).

The creation of the required vacuum was carried out by a turbomolecular pump; created a vacuum from 10 ^-5 to 10 ^-7 mm Hg

The total thickness of the coating of the prototype and the coating applied by the proposed method ranged from 7 μm to 15 μm.

Electrolyte-plasma polishing was carried out by immersing the parts in an aqueous electrolyte solution and applying an electric voltage positive with respect to the electrolyte, carrying out the following options: polishing was carried out until the roughness was not lower than R _a = 0.08 ... 0.12 μm; polishing was carried out at an operating voltage of 18..490 V; as options, the electrolyte used was: an aqueous solution of ammonium sulfate with a concentration of 0.8 ... 3.4; an aqueous solution containing sulfuric and phosphoric acid, a block copolymer of ethylene and propylene oxides and the sodium salt of sulfonated butyl oleate in the following ratio, wt.%:

Sulfuric acid - 10-30

Orthophosphoric acid - 40-80

Block copolymer of ethylene oxide and propylene - 0.05-1.1

Sodium salt of sulfonated butyl oleate - 0.01-0.05

Water - The rest.

As options, the following were used as the electrolyte: aqueous solutions of salts of inorganic acids of ammonium and alkali metals or salts of lower carboxylic acids, as well as solutions of free acids; an electrolyte containing an ammonium salt of an inorganic acid, ammonium salts of lower carboxylic acids, and organic or inorganic substances forming complex compounds with alloy metals; use an electrolyte composition, wt.%:

(NH ₄ ) ₂ SO ₄ - 5

Trilon B - 0.8.

Alternatively, the electrolyte used was: electrolyte composition,

wt.%:

(NH ₄ ) ₃ PO ₄ - 5

H ₃ PO ₄ - 0.5

Tartrate K - 0.5;

As an option, the following were used as the electrolyte: aqueous solutions of sodium salts; as an aqueous solution of sodium salts, a 3-22% solution of sodium hydrogencarbonate is used. As the electrolyte used: aqueous solutions of ammonium salts; as the ammonium salt, ammonium citrate is used, one or two, or trisubstituted, or mixtures thereof in the following ratio of components, wt.%: Ammonium citrate, mono- or two- or trisubstituted, or mixtures thereof - 2-18

Water - The rest.

As an option, used as an electrolyte: aqueous solutions of salts with a pH value of 4 ... 9.

Tests for endurance and cyclic strength of samples from the above grades of steels and alloys in air showed that the conditional endurance limit (σ _-1 ) of samples processed according to the variants of the proposed method exceeds, on average, the value of the conditional endurance limit of samples processed by the method prototype [A.S. USSR No. 1478520, IPC B23H 5/06, Method for dimensional electrochemical processing of GTE blades. Publ. September 20, 2005] from 1.1 to 1.4 times.

Example 2. The workpiece was subjected to the preparation of turbomachine blades made of titanium alloys of grades VT-1, VT-5, VT6, VT14, VT3-1, VT22. To do this, they were placed in the cavity of the cathode-instrument, immersed in a bath with an aqueous solution of electrolyte, and then applying a positive voltage to the part, and a negative voltage to the electrolyte, they were processed. The billets were processed in an electrolyte based on an aqueous solution, which included salts of hydrofluoric, silicofluoric, hexafluorotitanic or hydrofluoric acids (NH ₄ BF ₄ ; No. 2 SiF ₆ ). In addition, we used aqueous solutions of electrolytes containing (8% -12%) NaNO ₃ with the addition of surfactants from 2 to 8 g / m ³ .

After dimensional processing, the parts were subjected to electrochemical polishing. At the initial microroughness height of 0.63 microns after the polishing process, it was 0.10 microns.

Next, the workpieces from these titanium alloys were subjected to hardening treatment as in the prototype method [A.S. USSR No. 1478520, IPC B23H 5/06, Method for dimensional electrochemical processing of GTE blades. Publ. September 20, 2005], according to the processing conditions and modes described in the prototype method, and according to the proposed method of ion-implantation hardening treatment.

Modes of processing samples for the proposed method.

Ion purification: argon ions at an energy of 6 keV - unsatisfactory result (N.R.); 8 keV - satisfactory result (U.R.); 10 keV (U.R.); 12 keV (N.R.); current density: 110 MkA / cm ² (N.R.); 130 MkA / cm ² (U.R.); 160 MkA / s ² (U.R.); 180 MkA / cm ² (N.R.); ion cleaning time: 0.1 hours (N.R.); 0.3 hours (U.R.); 1.0 hours (U.R.); 1.5 hours (N.R.).

Ion implantation with Cr, V, Y, Yb, C, B, Zr, N, La, Ti ions and their combinations: energy - 20 keV - Unsatisfactory result (N.R.); 25 keV - Satisfactory result (U.R.); 30 keV (U.R.); 40 keV (N.R.); dose - 1.2 · 10 ¹⁷ cm ^-2 (N.R.); 1.6 · 10 ¹⁷ cm ^-2 (U.R.); 2 · 10 ¹⁷ cm ^-2 (U.R.); 3 · 10 ¹⁷ cm ^-2 (N.R.); dose rate - 0.4 · 10 ¹⁵ s ^-1 (N.R.); 0.7 · 10 ¹⁵ s ^-1 (U.R.); 1 · 10 ¹⁵ s ^-1 (U.R.); 3 · 10 ¹⁵ s ^-1 (N.R.).

The creation of the required vacuum was carried out by a turbomolecular pump; created a vacuum from 10 ^-5 to 10 ^-7 mm Hg

After processing the parts, postimplantation annealing was performed in one vacuum volume of the installation in one technological cycle.

Ion implantation was performed both in pulsed and continuous modes.

Shot blasting and coating were performed according to the same modes and with the same parameters as in the above example (see Example 1).

As parts from titanium alloys, the compressor blades of a gas turbine engine, the blades of a gas turbine plant and the blades of a steam turbine were used.

The endurance and cyclic strength tests of samples of titanium alloys in air were carried out. As a result of the experiment, the following was established: conditional endurance limit

(σ _-1 ) samples in the initial state is 400 MPa, for samples hardened by the prototype method - 420 MPa, and according to the proposed method 440-480 MPa.

Thus, the comparative tests showed that the use of the following techniques in the method of processing a blade of a gas turbine engine: simultaneous electrochemical formation of the profile of the pen and the nibble site; hardening treatment by ion implantation at an energy of 25 to 30 keV, a dose of 1.6 · 10 ¹⁷ cm ^-2 to 2 · 10 ¹⁷ cm ^-2 , with a dose rate of 0.7 · 10 ¹⁵ s ^-1 to 1 · 10 ¹⁵ s ^-1 ; as ions, ions of Cr, V, Y, Yb, C, B, Zr, N, La, Ti, or combinations thereof are used; ion-implantation hardening treatment is carried out after the electrochemical formation of the profile of the pen and the adjacent site; before ion-implantation hardening treatment is carried out: either electrochemical polishing or electrolyte-plasma polishing; before polishing, a shot peening is carried out, while the ratio of the diameter of the shot to the radius of the outlet edge of the feather blade is selected within 0.3 ... 4, and after shot peening, the surface layer with a thickness of 0.04 ... 0.3 of the depth of the riveted layer is removed; after polishing, before hardening ion-implantation treatment, shot peening is carried out with a flow of microspheres with a diameter of 10 ... 80 microns at a speed of 10 ... 30 m / s; ion implantation is carried out either in a pulsed mode or in a continuous mode, and after ion-implantation hardening treatment, post-implantation annealing is performed; as gas turbine engine parts, compressor blades of a gas turbine engine made of high alloy steels or titanium alloys are used; after ion-implantation hardening treatment by the ion-plasma method, a coating is applied: either from superhard compounds of one of the refractory metals of groups IV-VI of the Periodic system of elements (Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W) with N, C, B or Si, or a multilayer coating of alternating layers of Me and metal compounds with nitrogen - Me-N, carbon Me-C or carbon and nitrogen - Me-NC, where Me is Ti, Zr, TiZr, and N is nitrogen, C is carbon, they make it possible to achieve the technical result set in the inventive method - to increase the fatigue strength of GTE blades.

Claims (18)

1. The method of processing the blades of a gas turbine engine, including the simultaneous electrochemical formation of the profile of the pen and the glue section, hardening treatment, characterized in that the hardening treatment is carried out by ion implantation at an energy of 25 to 30 keV, a dose of 1.6 · 10 ¹⁷ cm ^-2 up to 2 · 10 ¹⁷ cm ^-2 and with a dose rate from 0.7 · 10 ¹⁵ s ^-1 to 1 · 10 ¹⁵ s ^-1 , using ions Cr, V, Y, Yb, C, B, Zr, N , La, Ti, or combinations thereof, and ion-implantation hardening treatment is carried out after the electrochemical formation of the pen profile and nibble on site. 2. The method according to claim 1, characterized in that prior to the ion-implantation hardening treatment, polishing is carried out by the electrochemical method or by the electrolyte-plasma method. 3. The method according to claim 2, characterized in that the shot blast hardening is carried out before polishing, while the ratio of the diameter of the shot to the radius of the outlet edge of the feather blade is selected within 0.3 ... 4, and when polishing the surface layer with a thickness of 0.04 ... 0 is removed , 3 depths of riveted layer. 4. The method according to claim 2, characterized in that after polishing, before hardening the ion implant treatment, shot peening is carried out with a flow of microspheres with a diameter of 10 ... 80 μm at a speed of 10 ... 30 m / s. 5. The method according to any one of claims 1 to 4, characterized in that the ion implantation is carried out in a pulsed mode or in a continuous mode. 6. The method according to any one of claims 1 to 4, characterized in that after ion-implantation hardening treatment, post-implantation annealing is carried out. 7. The method according to claim 5, characterized in that after ion-implantation hardening treatment, post-implantation annealing is performed. 8. The method according to any one of claims 1 to 4, 7, characterized in that the details of the gas turbine engine are used in the form of compressor blades of a gas turbine engine made of high alloy steels or titanium alloys. 9. The method according to claim 5, characterized in that the gas turbine engine parts are used in the form of compressor blades of a gas turbine engine made of high alloy steels or alloys or titanium alloys. 10. The method according to claim 6, characterized in that the details of the gas turbine engine are used in the form of compressor blades of a gas turbine engine made of high alloy steels or alloys or titanium alloys. 11. The method according to any one of claims 1 to 4, 7, 9, 10, characterized in that after the ion-implantation hardening treatment by the ion-plasma method, a coating is made of superhard compounds of one of the refractory metals of groups IV-VI of the Periodic system of elements: Ti Zr, Hf, V, Nb, Ta, Cr, Mo, W with N, C, B or Si. 12. The method according to claim 5, characterized in that after ion-implantation hardening treatment by the ion-plasma method, a coating is made of superhard compounds of one of the refractory metals of groups IV-VI of the Periodic Table of the Elements: Ti, Zr, Hf, V, Nb, Ta , Cr, Mo, W with N, C, B or Si. 13. The method according to claim 6, characterized in that after the ion-implantation hardening treatment by the ion-plasma method, a coating is made of superhard compounds of one of the refractory metals of groups IV-VI of the Periodic Table of the Elements: Ti, Zr, Hf, V, Nb, Ta , Cr, Mo, W with N, C, B or Si. 14. The method according to claim 8, characterized in that after the ion-implantation hardening treatment by the ion-plasma method, a coating is made of superhard compounds of one of the refractory metals of groups IV-VI of the Periodic system of elements: Ti, Zr, Hf, V, Nb, Ta , Cr, Mo, W with N, C, B or Si. 15. The method according to any one of claims 1 to 4, 7, 9, 10, characterized in that after the ion-implantation hardening treatment by the ion-plasma method, a multilayer coating is applied of alternating layers of Me and metal compounds with nitrogen - Me-N, carbon Me-C or carbon and nitrogen - Me-NC, where Me is Ti, Zr, TiZr, a N is nitrogen, C is carbon. 16. The method according to claim 5, characterized in that after the ion-implantation hardening treatment by the ion-plasma method, a multilayer coating is applied of alternating layers of Me and metal compounds with nitrogen - Me-N, carbon Me-C or carbon and nitrogen - Me- NC, where Me is Ti, Zr, TiZr, N is nitrogen, C is carbon. 17. The method according to claim 6, characterized in that after hardening treatment by the ion-plasma method, a multilayer coating is applied of alternating layers of Me and metal compounds with nitrogen - Me-N, carbon Me-C or carbon and nitrogen - Me-NC, where Me is Ti, Zr, TiZr, N is nitrogen, C is carbon. 18. The method according to claim 8, characterized in that after hardening treatment by the ion-plasma method, a multilayer coating is applied of alternating layers of Me and metal compounds with nitrogen - Me-N, carbon Me-C or carbon and nitrogen - Me-NC, where Me is Ti, Zr, TiZr, N is nitrogen, C is carbon.