JP6847059B2 - Blades of turbomachines with protective structures, turbomachines, and methods of forming protective structures - Google Patents

Description

Embodiments of the subject matter disclosed herein correspond to blades of turbomachinery with protective structures, turbomachinery (particularly steam turbines), and methods of forming protective structures.

During operation, the blades of turbomachinery often suffer from erosion.

In particular, the blades of steam turbines are often eroded by droplets.

Structures for protecting turbomachinery blades from erosion, corrosion, or wear can consist of layers formed on the surface of the blades or inserts fitted into the body of the blades.

The protective layer can be formed, for example, by laser cladding or cold spraying. Both of these techniques are effective. In any case, laser cladding can heat the blade and cause, for example, residual stress and / or distortion of the blade, which can contribute to "stress corrosion cracking", while cold spraying on the blade Collisions can cause, for example, erosion of the blade edges during layer formation. Note that laser cladding is more expensive than cold spray, but faster.

U.S. Patent Application Publication No. 2014/272166

Therefore, it is generally required to improve the protective structure of the blades of turbomachinery and the method of forming the same.

This need is for "oil and gas" (ie, machinery and facilities for oil and / or gas exploration, production, storage, refining, and distribution) and "energy" (ie, machinery and facilities for power generation). Extremely strong for steam turbine blades in the field.

A first embodiment of the subject matter disclosed herein relates to a blade of a turbomachine.

According to such an embodiment, a blade of a turbomachine having a wing-shaped portion having front and trailing edges and first and second sides connecting the leading and trailing edges. It has a protective structure that includes a protective edge and first and second protective stripes, the protective edge is located on the front edge and the first protective stripe is located on the first side surface and adjacent to the edge. , The second protective stripe is located on the second side and adjacent to the edge, the edge is laser cladding or welding, plasma spraying, detonation spraying, wire arc spraying, flame spraying, fast oxygen fuel coating spraying, or The blades of a turbomachine, formed by warm spraying and the first and second stripes are formed by cold spraying, are provided.

A second embodiment of the subject matter disclosed herein relates to a turbomachine.

According to such an embodiment, the turbomachinery, in particular the steam turbine, comprises the blades of the plurality of turbomachinery as described above.

A third embodiment of the subject matter disclosed herein relates to a method of forming a protective structure.

According to such an embodiment, the method of forming a protective structure on the blades of a turbomachinery involves the following consecutive steps: (A) connecting the front and trailing edges and the leading and trailing edges. A step of preparing a blade of a turbomachine with an airfoil having one and a second side surface, (B) a step of forming a protective edge on the front edge by laser cladding, and (C) at least one spray nozzle. Includes the step of forming first and second protective stripes on the first and second flanks adjacent to the edges by cold spraying by.

The accompanying drawings incorporated herein and forming an integral part of the present specification show typical embodiments of the present invention, and these embodiments will be described in conjunction with a detailed description. ..

A schematic side view of an embodiment of a turbomachinery blade before forming a protective structure is shown. A schematic side view of an embodiment of a turbomachinery blade during the formation of a protective structure is shown. A schematic side view of an embodiment of a turbomachinery blade after the formation of a protective structure is shown. The details of FIG. 3 are shown schematically. The cross-sectional view of FIG. 4 is shown schematically. A schematic cross-sectional view of a portion of an embodiment of a turbomachinery blade before forming a protective structure is shown. A schematic cross-sectional view of a portion of an embodiment of a turbomachinery blade during the formation of a protective structure (first intermediate stage) is shown. A schematic cross-sectional view of a portion of an embodiment of a turbomachinery blade during the formation of a protective structure (second intermediate stage) is shown. A schematic cross-sectional view of a portion of an embodiment of a turbomachinery blade after the formation of a protective structure is shown. A schematic side view of an embodiment of a turbomachinery blade after forming a protective structure in the alternative manner of FIG. 3 is shown. A schematic cross-sectional view of a first portion considered for an embodiment of a turbomachinery blade after the formation of a protective structure is shown. A schematic cross-sectional view of a second portion considered for one embodiment of a turbomachinery blade after the formation of a protective structure is shown. A schematic cross-sectional view of a third portion considered for one embodiment of a turbomachinery blade after the formation of a protective structure is shown. A schematic cross-sectional view of a fourth portion considered for one embodiment of a turbomachinery blade after the formation of a protective structure is shown.

For a description of typical embodiments below, reference is made to the accompanying drawings.

The following description is not limited to the present invention. Instead, the scope of the invention is defined by the appended claims.

Throughout this specification, reference to "one embodiment" or "embodiment" is at least one of the subjects in which a particular feature, structure, or property described in connection with an embodiment is disclosed. Means included in one embodiment. Therefore, the appearance of "in one embodiment" or "in an embodiment" in various places throughout the specification does not necessarily refer to the same embodiment. In addition, individual features, structures, or properties may be combined in any suitable manner in one or more embodiments.

FIG. 1 shows a schematic side view of a blade 1 of a turbomachine before forming a protective structure. The blade 1 is an airfoil having a front edge 3 and a trailing edge 4 and a first side surface 5 and a second side surface 6 (shown only in FIG. 5) connecting the front edge 3 and the trailing edge 4. It has a part 2. The airfoil portion 2 has a tip region 21 and a base region 22, and the base region 22 of the airfoil portion 2 is adjacent to the base 10 of the blade 1.

3, FIG. 4, and FIG. 5 show the blade 1 after the protective structure is formed. The protective structure comprises a protective edge 7 (which may also be referred to as a "bumper" or "buffer") and a first protective stripe 8 and a second protective stripe 9 (shown only in FIG. 5). 7 is located on the front edge 3, the first protective stripe 8 is located on the first side surface 5 and adjacent to the edge 7, and the second protective stripe 9 is preferably on the second side surface 6. It is located only in and adjacent to the edge 7.

In the embodiment of FIG. 5, the stripes 8 and 9 do not cover the edge 7 and are located only on the sides 5 and 6, respectively.

In the embodiment of FIG. 9, the stripes 8 and 9 are located on the sides 5 and 6, respectively, but also cover the entire edge 7, and the thickness of the stripes 8 and 9 gradually decreases on the edge 7. , Zero (or nearly zero) at the center of edge 7.

In the embodiment of FIG. 11 (similar to FIG. 5), the two stripes do not cover the edge 171 and are each located only on the two sides of the airfoil.

In the embodiment of FIG. 12 (similar to FIG. 9), the two stripes are located on the two sides of the airfoil, respectively, but also partially cover the edge 172, and the thickness of the stripe is the edge. It gradually decreases above and is zero (or nearly zero) in the center of the rim.

In the embodiment of FIG. 13, the two stripes are located on the two sides of the airfoil, respectively, but also completely cover the edge 173, with the stripe thickness gradually decreasing on the edge. The smallest and smallest in the center of the rim.

In the embodiment of FIG. 14, the two stripes are located on the two sides of the airfoil, respectively, but also completely cover the edge 173, with the stripe thickness gradually decreasing on the edge. Smallest and largest in the center of the rim.

According to these embodiments, the edges of the protective structure project from the anterior edge of the airfoil portion of the blade. The protrusion (at the end of blade manufacturing) depends on the manufacturing process (eg, the degree of cold spray erosion). Considering the warp line of the airfoil (100 in FIGS. 11-14) and its extension, the protrusion may be, for example, in the range of 0.05 to 1 mm.

(Such as previous example cold spray, immediately after forming) the cross-sectional area of the edges, the manufacturing process (e.g., the degree of erosion cold spray) must take into account the, be in a range of 1 mm ² to 20 mm ² it may be more typically in the range of 4 mm ² to 10 mm ^2. The cross-sectional area of the edges (eg, before cold spray, immediately after formation) must take into account the manufacturing process (eg, the degree of erosion by cold spray) and may look like a bulge.

The outer shape of the blade airfoil at the end of blade manufacturing depends on the outer shape of the blade airfoil before the formation of the protective structure and the protective structure covering it, especially during the formation of protective edges and protective stripes. Depends on protective edge erosion. Therefore, at least the front edge of the blade airfoil before the formation of the protective structure should be manufactured slightly recessed with respect to the ideal position of the blade airfoil front edge at the end of blade manufacturing. Is.

The technical solution according to the above-described embodiment is particularly useful for thin blades, for example blades with a thin leading edge in the range of 4-8 mm.

As will be better described later, the edges of the protective structure can be laser cladding or welding, plasma spraying, detonation spraying, wire arc spraying, flame spraying, fast oxygen fuel coating spraying, or warm spraying (preferably laser cracking). The first and second stripes of the protective structure are formed by cold spraying, while they are formed by the ding).

The airfoil portion of the blade may be made of iron, titanium, nickel-based alloy, or stainless steel, preferably made of stainless steel, such as AISI 420.

The edges of the protective structure may be made of a cobalt-based alloy or a cobalt-chromium alloy, preferably a Stellite-type material, in particular Stellite 6, Stellite 12, or Stellite 21, Ultimate, patent application. It is made of either the material described in EP14033397 and claimed for patent, or the material described in patent application EP1403398 and claimed for patent. The edge material is more resistant to solid particle erosion than the airfoil material because it is better resistant to mechanical erosion by cold spray.

The first and second stripes of the protective structure may be made of a cobalt-based alloy or a cobalt-chromium alloy, preferably a stellite-type material, in particular Stellite 6, Stellite 12, or Stellite 21, Ultimate, patent application. It is made of either the material described in EP14033397 and claimed for patent, or the material described in patent application EP1403398 and claimed for patent. The material of the first and second stripes resists erosion by droplets. The material of the first and second stripes may be the same as or different from the material of the edges.

The edges of the protective structure and the first and second stripes of the protective structure can extend over a portion of the height of the airfoil of the blade (ie, preferably from 20% to preferably 50%) (eg, figure). 3 and FIG. 10). Typically, the upper end of the stripe is located at the tip of the airfoil and the lower end of the stripe is located in the middle of the airfoil. Preferably, the edges of the protective structure are the same length as the first and second stripes of the protective structure, or slightly longer than the first and second stripes of the protective structure. The height of the airfoil is the portion of the blade that extends from the tip to the base of the blade.

The first and second stripes of the protective structure can extend over a portion of the width of the airfoil of the blade (ie, preferably from 5% to preferably 50%) (see, eg, FIGS. 3 and 10). ). Typically, the stripes extend from the anterior edge of the airfoil of the blade. The width of the airfoil is the portion of the blade that extends from the front edge to the trailing edge.

Blades that are the same as or similar to the blades just described can be conveniently used in turbomachinery in the fields of "oil and gas" and "energy". In particular, steam turbines are ideal applications because of their resistance to droplet erosion.

Protective structures that are the same as or similar to the protective structures just described (see FIGS. 3 and 4 and 10) have the following consecutive steps: A) leading and trailing edges and leading and trailing edges. A step of preparing a blade of a turbomachine (see, eg, FIGS. 1 and 6) having an airfoil having first and second sides to be connected.
B) The step of forming a protective edge on the leading edge by laser cladding (see, eg, FIGS. 2 and 7), and
C) First on the first and second sides adjacent to the edges by cold spraying with at least one spray nozzle, which is a highly effective way to form a thin and well-adhered material layer that withstands erosion. And the step of forming the second protective stripe (see, eg, FIG. 3 and FIG. 5 or FIG. 9).
Can be formed on the blades of turbomachinery.

In this way, the anterior edge of the airfoil is protected by the edge and the cross section of the airfoil is well covered by cold spray both laterally and anteriorly.

This is especially advantageous for thin blades, more specifically for blades with a thin leading edge, where the "thin leading edge" can have a thickness in the range of, for example, 2-10 mm and of the leading edge. If the cross section resembles a semicircle, the "thin leading edge" can have radii in the range of, for example, 1-5 mm.

In this way, there is very little heating of the blade by laser cladding, and thus very little residual stress and distortion in the blade and "stress corrosion cracking" in the blade.

Instead of laser cladding, welding, plasma spraying, detonation spraying, wire arc spraying, flame spraying, high speed oxygen fuel coating spraying, or warm spraying can be used.

The same spray nozzle can be used to form both protective stripes. Alternatively, the first spray nozzle may be used to form the first protective stripe and the second spray nozzle may be used to form the second protective stripe, in which case the first and second protective stripes. May be formed at the same time.

The stripes of the protective structure can include multiple parallel (or substantially parallel) segments. In FIGS. 4-9, the segments 81 and 91 are lateral (particularly perpendicular) to the front edge 3. In FIGS. 10-14, the segment 181 is parallel (or substantially parallel) to the leading edge 103. Note that these segments come into contact with each other laterally, even if they are shown apart in FIGS. 4 and 10.

The spray nozzle moves from at least the side surface (eg, 5 or 6) of the airfoil to the edge (eg, 7) to form a stripe (eg, 8 or 9), preferably the front edge (eg, 7). Rotate at least 40 ° around the leading edge (eg, 3) to form a stripe (eg, 8 or 9) adjacent to 3) and the edge (eg, 7). In the first part of the spray nozzle movement, the spray jet is oriented highly tilted (preferably perpendicular) to the (side) surface of the airfoil, as the spray nozzle approaches the leading edge. The spray nozzle is gradually rotated so that the spray jet remains in a highly tilted (preferably vertical) orientation with respect to the (front) surface of the airfoil.

As a first option, step C (eg, consider FIGS. 6-9)
The spray nozzle moves from the first side surface (eg, 5) of the airfoil to the edge (eg, 70, 71, 72) and rotates at least 40 °, preferably 80-90 °. First substep C1A (see FIG. 8) forming a segment (eg, 81) of a stripe (eg, 8) of
Can include, immediately after that,
The spray nozzle moves from the second side surface (eg, 6) of the airfoil to the edge (eg, 70, 71, 72) and rotates at least 40 °, preferably 80-90 °, so that the second Second substep C2A (see FIG. 9) forming a segment (eg, 91) of stripes (eg, 9).
Can include,
Preferably, during substeps C1A and C2A, the spray nozzle maintains a constant longitudinal position on the airfoil.

In this way, two separate segments are formed at the same height on the two sides of the airfoil.

If substeps C1A and C2A are repeated several times at different heights, two stripes will be formed simultaneously on the two sides of the airfoil.

As a second option, step C
The spray nozzle moves from the first side surface (eg, 5) of the airfoil to the edge (eg, 70, 71, 72) and rotates at least 40 °, preferably 80-90 °. First substep C1B forming a segment (eg, 81) of a stripe (eg, 8) of
Can include, immediately after that,
The same first spray nozzle is rotated by at least 40 °, preferably 80-90 °, and moves away from the edge (eg, 7) to the first side surface (eg, 5) of the airfoil. Second substep C2B (see FIG. 9) forming another segment (eg 81) of the stripes (eg 8).
Can include,
Preferably, during sub-steps C1B and C2B, the spray nozzle maintains a constant longitudinal position on the airfoil, and the spray nozzle is slightly longitudinally after sub-step C1B and before sub-step C2B. Is displaced to.

In this way, in the two manufacturing operations, two parallel segments are formed at different heights on the same side of the airfoil.

When substeps C1B and C2B are repeated several times, one stripe is formed on one side surface of the airfoil portion. After that, another stripe is formed on the other side of the airfoil.

As a third option, step C
The spray nozzle moves from the first side surface (eg, 5) of the airfoil to the edge (eg, 7) to form a segment (eg, 81) of the first stripe (eg, 8). First substep C3,
A second substep C4 in which the same spray nozzle rotates 80-180 ° around the leading edge (eg, 3) to form a (typically thin) connecting segment, and the same spray nozzle is airfoiled. A third that forms a segment (eg, 91) of the second stripe (eg, 9) by moving away from the edge (eg, 7) towards the second side surface (eg, 6) of the portion. Substep C5
Can include,
Preferably, during substeps C3, C4, and C5, the spray nozzle maintains a constant longitudinal position on the airfoil.

In this way, two consecutive segments are formed at the same height on the two sides of the airfoil.

If substeps C3, C4, and C5 are repeated several times at different heights, two stripes will be formed simultaneously on the two sides of the airfoil.

According to the third option, step C, after substep C5, has the following substeps, i.e., the same spray nozzle from the second side surface (eg, 6) to the edge (eg, 7) of the airfoil. Fourth substep C6, which forms a segment of a second stripe (eg, 9) adjacent to the preceding segment by moving towards.
A fifth substep C7, in which the same spray nozzle rotates 80-180 ° around the leading edge (eg, 3) to form a (typically thin) connecting segment, and the same spray nozzle is airfoiled. A sixth segment that forms a segment of the first stripe (eg, 8) adjacent to the preceding segment by moving away from the edge (eg, 7) towards the first side surface (eg, 5) of the portion. Substep C8
Can further include,
Preferably, the spray nozzle is slightly displaced in the longitudinal direction after substep C5 and before substep C6.

Preferably, during substeps C6, C7, and C8, the spray nozzle maintains a constant longitudinal position in the airfoil.

In this way, two additional segments (adjacent to the first two segments) are formed at the same height on the two sides of the airfoil.

If substeps C3, C4, C5, C6, C7, and C8 are repeated several times at different heights, two stripes will be formed simultaneously on the two sides of the airfoil.

1 Turbomachinery blade 2 Airfoil 3 Front edge 4 Rear edge 5 First side surface 6 Second side surface 7 Protective edge 8 First protective stripe 9 Second protective stripe 10 Base 21 Tip area 22 Base area 70 Protection Edge 71 Protective Edge 72 Protective Edge 81 Segment 91 Segment 100 Warp Line 101 Blade 102 Airfoil 103 Front Edge 104 Rear Edge 107 Protective Edge 108 First Protective Stripe 171 Protective Edge 172 Protective Edge 173 Protective Edge 174 Protective Edge 181 Segment

Claims (20)

An airfoil portion (2) having a front edge (3) and a trailing edge (4) and first and second side surfaces (5, 6) connecting the front edge (3) and the trailing edge (4). ) Is a turbomachinery blade (1), comprising a protective structure including a protective edge (7) and first and second protective stripes (8, 9).
The protective edge (7) is located at the front edge (3).
The first protective stripe (8) is located on the first side surface (5) and adjacent to the protective edge (7).
The second protective stripe (9) is located on the second side surface (6) and adjacent to the protective edge (7).
The protective edge (7) is formed by laser cladding or welding, plasma spraying, detonation spraying, wire arc spraying, flame spraying, high speed oxygen fuel coating spraying, or warm spraying.
The first and second protective stripes (8, 9) are formed by cold spray, and each of the first and second protective stripes (8, 9) has a plurality of parallel streaky segments. , Turbomachinery blade (1). The airfoil portion (2) is made of iron, titanium, nickel-based alloy, or stainless steel.
The blade (1) of the turbomachine according to claim 1. The protective edge (7) is made of a cobalt-based alloy or a cobalt-chromium alloy.
The blade (1) of the turbomachine according to claim 1 or 2. The first and second protective stripes (8, 9) are made of a cobalt-based alloy or a cobalt-chromium alloy.
The blade (1) of the turbomachine according to any one of claims 1 to 3. The protective edge (7) and the first and second protective stripes (8, 9) range from 20% to 50% of the height of the airfoil (2).
The blade (1) of the turbomachine according to any one of claims 1 to 4. The first and second protective stripes (8, 9) extend from 5% to 50% of the width of the airfoil (2).
The blade (1) of the turbomachine according to any one of claims 1 to 5. Any of claims 1 to 6, wherein in the first and second protective stripes (8, 9), the plurality of parallel streaky segments extend laterally or parallel to the front edge (3). The blade (1) of the turbomachine according to item 1. Claims 1 to 7 in which the length of the protective edge (7) is equal to or greater than the length of the first and second protective stripes (8, 9) in the height direction of the airfoil portion (2). The blade (1) of the turbomachine according to any one of the above items. Claims 1 to 1, wherein at least one segment of the first protective stripe (8) and at least one segment of the second protective stripe (9) are formed at substantially the same height. The blade (1) of the turbomachine according to any one of 8. Turbo machinery comprising a blade (1) of the plurality of turbomachine according to any one of claims 1 to 9. The turbomachine according to claim 10, which is a steam turbine. An airfoil portion having a front edge (3) and a trailing edge (4) and first and second side surfaces (5, 6) connecting the front edge (3) and the trailing edge (4). A method of forming a protective structure on a blade (1) of a turbomachine provided with 2), the following consecutive steps, ie.
Step of forming a protective edge (7) on the front edge (3) by Les chromatography The cladding and,
The cold spray according SPRAY nozzle, forming first and second protective stripe (8,9) on the adjacent first and second side surfaces (5, 6) in said protective rim (7) ,
Only it contains each of the first and second protective stripe (8,9) has a plurality of parallel stripe-shaped segments, methods. The first protective stripe (8) is formed before the second protective stripe (9), after the second protective stripe (9), or at the same time as the second protective stripe (9). The method according to claim 12. 12. The method of claim 12 or 13 , wherein the first or second protective stripe (8, 9) comprises a plurality of parallel segments (81, 91) laterally relative to the front edge (3). .. In the step of forming the first and second protective stripes (8, 9) , the spray nozzle moves from the side surface (5, 6) of the airfoil portion toward the protective edge (7), and at least. 40 ° rotation, the method according to any one of claims 12 to 14. The steps of forming the first and second protective stripes (8, 9) are
The spray nozzle moves from the first side surface (5) of the airfoil portion (2) toward the protective edge (7) to move the segment (81) of the first protective stripe (8). First substep C3 to form,
A second sub-step C4 in which the spray nozzle rotates around the front edge (3) by 80 to 180 ° to form a connecting segment, and the second sub-step C4 in which the spray nozzle is the airfoil portion (2). A third sub-step C5 that forms a segment (91) of the second protective stripe (9) by moving toward the side surface (6) of the second protective stripe (7) in a direction away from the protective edge (7).
The method according to any one of claims 12 to 15 , which comprises. The step of forming the first and second protective stripes (8, 9) is the following sub-step after the third sub-step C5, that is, the spray nozzle is the second side surface of the airfoil portion. by moving toward said protective rim (7) from the fourth sub-step of forming a segment of the second protective stripe adjacent segments of earlier line C6,
A fifth sub-step C7, in which the spray nozzle rotates around the front edge by 80-180 ° to form a connecting segment, and the spray nozzle protects the airfoil from the first side surface. by moving away from the edge (7), the sixth sub-step of forming a segment of the first protective stripe adjacent to a segment of previously row C8
Including
16. The method of claim 16, wherein the spray nozzle is displaced in the longitudinal direction after the third substep C5 and before the fourth substep C6. The first or second protective stripe (108), said front including edge (103) a plurality of parallel segments parallel to the (181) A method according to any one of claims 12 to 17. In the first and second protective stripes (8, 9), the length of the protective edge (7) in the height direction of the airfoil portion (2) is the length of the first and second protective stripes (8, 9). 8. The method of any one of claims 12-18, which is formed to be equal to or greater than the length of 8 and 9). Claims 12 to 19 wherein at least one segment of the first protective stripe (8) and at least one segment of the second protective stripe (9) are formed at substantially the same height. The method according to any one of the above.

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