Work fixture for vacuum heat treatment of aero-engine turbine blade

Abstract

The invention provides a tool clamp for vacuum heat treatment of aero-engine turbine blades, and belongs to the technical field of vacuum heat treatment, the clamp comprises a first clamping block and a second clamping block which are used for clamping a blade to be clamped, and supporting blocks which are arranged on the first clamping block and the second clamping block and are used for being in contact with the blade to be clamped, one end of the first clamping block and one end of the second clamping block are connected through a hinge, the first clamping block and the second clamping block are made of high-temperature-resistant molybdenum-lanthanum alloy materials, and the supporting block is a high-temperature-resistant ceramic block. According to the tool clamp for vacuum heat treatment of the aero-engine turbine blade, the clamp made of the molybdenum-lanthanum alloy is adopted for replacing nickel-chrome wire hanging, the service life of the tool is prolonged, and the manual hanging time is saved; the surface of the inner cavity of the clamp main body is matched with the molded surface of the blade, and a gap is formed between the surface of the inner cavity and the molded surface of the blade, so that argon can freely flow on the surface of the blade during cooling, part pollution caused by mutual diffusion between a clamp material and the clamped blade is avoided, and part quality is ensured.

Description

Technical Field

[0001] The invention belongs to the technical field of vacuum heat treatment, and in particular relates to a tooling fixture for vacuum heat treatment of turbine blades of an aero-engine. Background Art

[0002] Turbine blades are the parts with the highest temperature and the most severe thermal shock among turbine components, and they have high requirements for materials. The most prominent requirement is that the material must have high resistance to oxidation and thermal corrosion at high temperatures, and at the same time have good resistance to thermal fatigue and thermal shock, as well as sufficient heat resistance. Usually, turbine blades are made of cast high-temperature alloys. Taking nickel-based cast high-temperature alloys as an example, methods to improve the high-temperature performance of alloys include solid solution strengthening (which refers to the addition of aluminum, titanium, niobium, tantalum, etc. that can form γ ′ Phase alloying elements are integrated into the alloy, causing a certain lattice distortion, thereby improving the strength of the alloy), precipitation strengthening (by increasing the content of some elements, the precipitated second phase can effectively inhibit the development and growth of metal material particles), etc. Therefore, solid solution treatment is one of its main heat treatment methods. By heating the material to a certain temperature, it reaches a uniform solid solution state, and then keeps it at this temperature for a period of time to dissolve the solute in the matrix as much as possible. Solid solution treatment can improve the high temperature strength and corrosion resistance of the blade material, improve the material's plasticity and toughness, and improve its ability to resist crack propagation. At the same time, vacuum heat treatment technology is used. Compared with ordinary heat treatment, it has the advantages of no oxidation, no decarburization, degassing, degreasing, good surface quality, small deformation, and excellent comprehensive mechanical properties of heat-treated parts.

[0003] Since the temperature of the solid solution and stress relief vacuum heat treatment process of turbine blades is relatively high, the solid solution temperature of such blades is usually 1200-1250℃, and the stress relief is around 1000℃. The blades will have a small amount of deformation during the heat treatment process. In the actual process, the deformation is controlled by controlling the heat treatment heating rate, the blade furnace loading method, and subsequent correction. Among them, the furnace loading method has a key influence on the blade deformation and heat treatment quality.

[0004] In the prior art, there are two main ways to load turbine blades into furnaces: laying flat, which results in a large deformation of the parts; hanging, such as Figure 2 As shown, the existing clamp 6 uses a handmade ceramic tube 8 with a nickel-chromium wire 7 to hang the blade 9 to be clamped on the fixture frame 5. The blade 9 to be clamped shakes greatly during air cooling, and parts are easily damaged; during the hanging process, it is necessary to first wear a nickel-chromium wire ceramic tube, and then load the blade and hang it on the fixture frame 5; and the nickel-chromium wire 7 is subjected to greater stress during high temperature, and is easy to break, resulting in damage to the blade, and the service life is extremely short, and it is often a disposable product, with high labor costs, time-consuming and labor-intensive production process, and low efficiency.

[0005] Therefore, it is necessary to provide a tool that can solve the problem of turbine blade loading. Summary of the invention

[0006] In order to solve various problems existing in the prior art of turbine blade furnace loading, the present invention provides a tooling fixture for vacuum heat treatment of aircraft engine turbine blades.

[0007] In order to achieve the above-mentioned purpose, the present invention provides the following technical solution: a tooling fixture for vacuum heat treatment of aircraft engine turbine blades, the fixture comprising: a first clamping block and a second clamping block for clamping the blade to be clamped, and a support block arranged on the first clamping block and the second clamping block for contacting the blade to be clamped, one end of the first clamping block and the second clamping block are connected by a hinge, the first clamping block and the second clamping block are made of high-temperature resistant molybdenum-lanthanum alloy material, and the support block is a high-temperature resistant ceramic block.

[0008] The fixture for vacuum heat treatment of aircraft engine turbine blades provided by the present invention also has the following characteristics: the hinge is connected by a hole-pin structure with clearance fit, and a cylindrical pin for fixing is provided in the hole-pin structure.

[0009] The fixture for vacuum heat treatment of aircraft engine turbine blades provided by the present invention also has the following characteristics: the first clamping block and the second clamping block are both provided with countersunk holes, and the support block is arranged in the countersunk holes.

[0010] The fixture for vacuum heat treatment of aircraft engine turbine blades provided by the present invention also has the following characteristics: an inner cavity is provided between the first clamping block and the second clamping block, and the inner cavity matches the body surface of the blade to be clamped and leaves a gap.

[0011] The tooling fixture for vacuum heat treatment of aircraft engine turbine blades provided by the present invention also has the following characteristics: the first clamping block is provided with a convex surface, which matches the blade basin of the blade to be clamped; the second clamping block is provided with a concave surface, which matches the back of the blade to be clamped.

[0012] The fixture for vacuum heat treatment of aircraft engine turbine blades provided by the present invention also has the following characteristics: the upper end of the support block is a spherical surface, and the spherical surface protrudes relative to the first clamping block and the second clamping block, and the height of the protrusion is 1mm-5mm.

[0013] The fixture for vacuum heat treatment of aircraft engine turbine blades provided by the present invention also has the following characteristics: there are four support blocks, which are symmetrically arranged on the first clamping block and the second clamping block.

[0014] The tooling fixture for vacuum heat treatment of aircraft engine turbine blades provided by the present invention also has the following characteristics: a receiving cavity is formed between the other ends of the first clamping block and the second clamping block, and the inner width of the receiving cavity is matched with the width of one end of the first clamping block and the second clamping block, and the receiving cavity is used to receive one end of another tooling fixture with the same structure.

[0015] The fixture for vacuum heat treatment of aircraft engine turbine blades provided by the present invention also has the following characteristics: the lanthanum content in the molybdenum-lanthanum alloy is 0.1%-0.5%.

[0016] Beneficial effects:

[0017] The tooling fixture for vacuum heat treatment of aircraft engine turbine blades provided by the present invention adopts a fixture made of molybdenum-lanthanum alloy to replace nickel-chromium wire hanging, thereby improving the service life of the tooling fixture and saving manual hanging time; the surface of the inner cavity of the fixture body matches the blade body surface and has a gap, ensuring that argon gas can flow freely on the blade surface during cooling, avoiding mutual diffusion between the fixture material and the clamped blade to cause part contamination, and ensuring part quality.

[0018] The fixture provided by the present invention for vacuum heat treatment of aircraft engine turbine blades has a long service life and an average number of uses of more than 500 times. The fixture provided by the present invention can be used to hang blades in about 30 seconds to complete the installation of a blade, which can save nearly 20 times the labor time cost and greatly improve production efficiency. At the same time, the special profile structure provided by the present invention can increase the number of parts loaded by 30%. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 A schematic diagram of the structure of the tooling provided in an embodiment of the present invention;

[0021] Figure 2 It is a schematic diagram of the hanging of the prior art;

[0022] Figure 3 A schematic diagram of the tooling installation provided by an embodiment of the present invention;

[0023] Figure 4 A schematic diagram of supporting points of a supporting block of a tool provided in an embodiment of the present invention;

[0024] Figure 5A schematic diagram of the placement of tooling provided in an embodiment of the present invention;

[0025] Among them, 1: first clamping block; 2: second clamping block; 3: support block; 4: cylindrical pin; 5: tooling frame; 6: existing clamp; 7: nickel-chromium wire; 8: ceramic tube; 9: blade to be clamped; 10: accommodating cavity; A: first supporting point; B: second supporting point; C: third supporting point; D: fourth supporting point. DETAILED DESCRIPTION

[0026] The present invention is further described in detail below in conjunction with the accompanying drawings and examples, but it should be noted that these implementation modes are not limitations of the present invention, and equivalent changes or substitutions in functions, methods, or structures made by ordinary technicians in the field based on these implementation modes are all within the scope of protection of the present invention.

[0027] In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the invention.

[0028] In addition, the terms "first", "second", "third", etc. are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0029] The terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to specific circumstances.

[0030] like Figure 1As shown, an embodiment of the present invention provides a tooling fixture for vacuum heat treatment of aircraft engine turbine blades, the fixture comprising: a first clamping block 1 for clamping a blade 9 to be clamped, a second clamping block 2, and a support block 3 arranged on the first clamping block 1 and the second clamping block 2 for contacting the blade 9 to be clamped, one end of the first clamping block 1 and the second clamping block 2 are connected by a hinge, the first clamping block 1 and the second clamping block 2 are made of high-temperature resistant molybdenum-lanthanum alloy material, and the support block 3 is a high-temperature resistant ceramic block.

[0031] The tooling fixture for vacuum heat treatment of aircraft engine turbine blades provided in the above embodiment uses a fixture made of molybdenum-lanthanum alloy to replace the nickel-chromium wire hanging fixture, which increases the life of the tooling fixture and saves manual hanging time.

[0032] In some embodiments, the hinge is connected by a hole-pin structure with clearance fit, and the hole-pin structure is provided with a cylindrical pin 4 for fixing. The cylindrical pin 4 is used to ensure the stability of the hinge assembly, the smooth rotation of the clamping block, and the quick and convenient loading and unloading of parts.

[0033] In some embodiments, both the first clamping block 1 and the second clamping block 2 are provided with countersunk holes, and the supporting block 3 is disposed in the countersunk holes.

[0034] In some embodiments, an inner cavity is provided between the first clamping block 1 and the second clamping block 2, and the inner cavity matches the body of the blade 9 to be clamped and a gap is left. The first clamping block 1 has a convex surface, and the convex surface matches the blade pot of the blade 9 to be clamped; the second clamping block 2 has a concave surface, and the concave surface matches the back of the blade 9 to be clamped. The inner cavity surface of the fixture body matches the blade body surface and there is a gap to ensure that argon can flow freely on the surface of the workpiece during cooling. After the part is installed, it does not contact the fixture body, which prevents the mutual diffusion of the part material and the fixture material and contamination of the blade surface.

[0035] In some embodiments, the upper end of the support block 3 is a spherical surface, and the spherical surface protrudes 2 relative to the first clamping block 1 and the second clamping block, and the height of the protrusion is 1mm-5mm. The support block 3 isolates the blade 9 to be clamped from the first clamping block 1 and the second clamping block 2 made of molybdenum-lanthanum alloy material, preventing the blade from contacting the molybdenum-lanthanum alloy and causing high-temperature diffusion between them, while ensuring the distance between them.

[0036] In some embodiments, there are four support blocks 3, which are symmetrically arranged on the first clamping block 1 and the second clamping block 2. The support points of the support blocks 3 are respectively the first support point A and the second support point B in contact with the blade pot, the third support point C and the fourth support point D in contact with the blade back.

[0037] In some embodiments, a receiving cavity 10 is formed between the other ends of the first clamping block 1 and the second clamping block 2, and the inner width of the receiving cavity 10 matches the width of one end of the first clamping block 1 and the second clamping block 2. The receiving cavity 10 is used to accommodate one end of another tooling fixture of the same structure.

[0038] In some embodiments, the lanthanum content in the molybdenum-lanthanum alloy is 0.1%-0.5%.

[0039] The tooling provided by any of the above embodiments is convenient for clamping the blades, and the blades can be clamped directly using the first clamping block and the second clamping block, and then placed on the tooling frame for subsequent operations. The tooling is also reusable.

[0040] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention shall be included in the protection scope of the present invention. The above description is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and variations can be made without departing from the technical principles of the present invention. These improvements and variations should also be regarded as the protection scope of the present invention.

Claims

1. A fixture for vacuum heat treatment of aircraft engine turbine blades, characterized in that: The clamp comprises: a first clamping block and a second clamping block for clamping the blade to be clamped, and a support block arranged on the first clamping block and the second clamping block for contacting the blade to be clamped. One end of the first clamping block and the second clamping block are connected by a hinge, The first clamping block and the second clamping block are made of high temperature resistant molybdenum-lanthanum alloy material. The supporting block is a high temperature resistant ceramic block.

2. The fixture for vacuum heat treatment of aircraft engine turbine blades according to claim 1, characterized in that: The hinge is connected by a hole-pin structure with clearance fit, and a cylindrical pin for fixing is arranged in the hole-pin structure.

3. The fixture for vacuum heat treatment of aircraft engine turbine blades according to claim 1, characterized in that: The first clamping block and the second clamping block are both provided with countersunk holes, and the supporting block is arranged in the countersunk holes.

4. The fixture for vacuum heat treatment of aircraft engine turbine blades according to claim 1, characterized in that: An inner cavity is provided between the first clamping block and the second clamping block, and the inner cavity matches the body surface of the blade to be clamped with a gap.

5. The fixture for vacuum heat treatment of aircraft engine turbine blades according to claim 4, characterized in that: The first clamping block is provided with a convex surface, which matches the blade pot of the blade to be clamped; the second clamping block is provided with a concave surface, which matches the blade back of the blade to be clamped.

6. The fixture for vacuum heat treatment of aircraft engine turbine blades according to claim 1, characterized in that: The upper end of the support block is a spherical surface, and the spherical surface protrudes relative to the first clamping block and the second clamping block, and the height of the protruding portion is 1mm-5mm.

7. The fixture for vacuum heat treatment of aircraft engine turbine blades according to claim 1, characterized in that: The supporting blocks are provided with four blocks, and the four supporting blocks are symmetrically arranged on the first clamping block and the second clamping block.

8. The fixture for vacuum heat treatment of aircraft engine turbine blades according to claim 1, characterized in that: An accommodating cavity is formed between the other ends of the first clamping block and the second clamping block, and the inner width of the accommodating cavity is equal to the width of one end of the first clamping block and the second clamping block.

9. The fixture for vacuum heat treatment of aircraft engine turbine blades according to claim 1, characterized in that: The lanthanum content in the molybdenum-lanthanum alloy is 0.1%-0.5%.

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