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Steam-turbine engine low-pressure stage working blade. RU patent 2506430.

IPC classes for russian patent Steam-turbine engine low-pressure stage working blade. RU patent 2506430. (RU 2506430):

F01D5/22 - Blade-to-blade connections, e.g. by shrouding

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FIELD: engines and pumps.

SUBSTANCE: steam-turbine working blade 20 comprises aerodynamic part 42 with root part 44 attached to one end of the latter. Shank 40 with slot lock and skewed axial inlet extends from root part 44. End part 46 is attached to aerodynamic part 42, opposite the root part 44. Band 48 is made integral with end part 46. Band 48 has first flat part 52, second flat part 54 and recess 56 arranged laterally between said first and second flat parts. Recess 56 is located below first flat part 52 at first end whereat first flat part and recess 56 adjoin and ups to second flat part 54 at second end whereat second flat part and recess adjoin. Second flat part 54 is elevated above first flat part 52. Band 48 is located at 10 to 30 degrees relative to end part 46.

EFFECT: increased rpm at steam-turbine low-pressure stage.

10 cl, 5 dwg

BACKGROUND OF THE INVENTION

The present invention relates generally to a working blade for the steam turbine, and more specifically, to a working blade with geometry, contributing to increased operating speeds, for use in the last stage of the part of low pressure steam turbine.

Channel flow of steam in the steam turbine in General is formed static casing and rotor. In this construction, a large number of fixed guide vanes are attached to the body in the form of a series of blades, located on a circle and held in an internal direction in channel flow of steam. Similarly, a large number of blades attached to the rotor in the form of a series of blades, located on a circle and held toward the outside in channel flow of steam. Stationary vanes and blades are alternating rows so that the number of stationary blades and located just behind him a number of rotor blades form a step. Fixed blades are the direction of the steam flow so that he entered located behind them a number of rotor blades at the correct angle. Airfoil blades extract energy from the steam, thus developing, the power required to bring in a rotation of the rotor and the connected equipment load.

As the water vapor through a steam turbine its pressure falls in each subsequent stage, until it reaches the required outlet pressure. Thus, the properties of water vapor, such as temperature, pressure, speed and moisture content will vary from row to row, because water vapor expands, passing along its trajectory. Therefore, in each row of blades uses paddles with aerodynamic profile that is optimized for the state of water vapor, corresponding to this number.

In addition to the state of water vapor, the blades are also made with regard to the centrifugal pressures they experience while working. In particular, large centrifugal loads are applied to the blades of high-speed rotation of the rotor, which, in turn, leads to the mechanical stresses in the blades. Reduction of the stress concentration in the blades of a problem of design, and this is especially true of the last rows of blades part of low pressure steam turbine blades have a greater size and weight of the larger size and are exposed to corrosive influences because of the humidity in a stream of water vapor.

This issue of the design of rotor blades for the part of low pressure turbines, reinforced by the fact that the aerodynamic profile of blades of the forces acting on the blades, the mechanical strength of the blades, their resonant frequency and thermodynamic performance. These considerations impose restrictions on the choice of airfoil blades, so the optimum aerodynamic profile of blades for a specific number is a matter of compromise between the mechanical and aerodynamic properties associated with the profile.

SHORT DESCRIPTION OF THE INVENTION

One aspect of the present invention offered blade steam turbine. Blade contains aerodynamic part, to one end of which is attached to the root part. From the root part of the departs shank with lock, which represents a shaft with a beveled axial input. The aerodynamic parts on the end opposite the root part, attached terminal part for a single whole that is bandage, with the first flat part, second flat part, hollow, located in the lateral direction between the first flat part and the second flat part. Deepening located below the first flat part on the first end, where the first flat part and deepening adjoin to each other. Deepening lifted up to the second flat part on the other end, where a second flat part and deepening adjoin to each other. The second planar part of elevated above the first flat part. Bandage is located at an angle relative to the end portion, and the angle is in the range of approximately 10 degrees to about 30 degrees.

In another aspect of the present invention offered the part of low pressure steam turbine. In this aspect of the present invention a number of blades of the last stage in steam turbines placed around the turbine wheel. Each blade of this series blades has aerodynamic part, the length of which is approximately 10,56 inches (26,82 cm) or more of this magnitude. To one end of the aerodynamic parts are attached to the root part, which passes shank with castle, and the shank is a shank with sloping axial input. The aerodynamic parts on the end opposite the root part, attached terminal part. In one piece with the end part is made brace, which is the first part of that hung over the side of a high pressure aerodynamic parts, and the second part, hung over the side of low pressure aerodynamic parts. A bandage is placed at an angle relative to the end portion, and the angle is in the range of approximately 10 degrees to about 30 degrees.

BRIEF DESCRIPTION OF DRAWINGS

Figure 1 presents a view of the axonometric in the context of partial steam turbine;

Figure 2 is a view of the axonometric blade of a steam turbine in accordance with one variant of execution of the present invention;

Figure 3 is an enlarged view of the axonometric shank with lock with sloping axial input depicted on the blade, shown in figure 2, in accordance with one variant of execution of the present invention;

Figure 4 is a side view of the axonometric, depicting a magnified view of the bandage, depicted in Figure 2, in accordance with one variant of execution of the present invention; and

Figure 5 presents a view of the axonometric, illustrating correlation of adjacent bands in accordance with one variant of execution of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

At least one embodiment of the present invention is described below, with reference to its use in connection with the operation of steam-turbine engine. In addition, at least one embodiment of the present invention is described below, with reference to the estimated size and contains a number of calculation of measurements. However, for professionals using the idea of the invention should be obvious that this invention is similarly applicable to any suitable turbine and/or motor. Also, for the professionals who use the idea of the invention should be obvious that this invention is similarly applicable to different scales of assessment for the size and/or settlement of measurements.

With reference to the drawings, Figure 1 shows a view of the axonometric in the context of partial steam turbine 10. Steam turbine 10 rotor contains 12 containing the shaft 14 and a number of separated axial impellers 18. Blades 20 mechanically attached to each impeller 18 rotor. More specifically, the blades are 20 rows that are in a circle around each impeller 18. Fixed blades 22 are on the circumference around the shaft of 14 and are located in the axial direction between adjacent rows of blades 20. Fixed blades 22 together with blades 20 form stage of the turbine and the limit of the channel passage of steam through a turbine 10.

When working water vapor 24 reaches into the inlet 26 turbines 10 and is channeled through the stationary vanes 22. Blades 22 direct water vapor 24 downstream to the blades 20. Water vapor 24 passes through the other stages, passing force blades 20 and causing rotation of the shaft 14. At least one end of the turbine 10 may act in the radial direction away from the rotor 12 and can be connected to the load or a mechanism (not shown), such as, but not limited to, the generator and/or another turbine. Accordingly, much unit can actually include several turbines that all coaxially connected to one and the same shaft 14. This node can, for example, contain high-pressure turbine, attached to the medium-pressure turbine, which is connected to the turbine low pressure.

In one embodiment of the present invention, and as shown in figure 1, the turbine 10 contains five steps outlined L0, L1, L2, L3 and L4. Step L4 is the first level and is the lowest (in the radial direction) of five steps. Step L3 is the second stage and is the next step in the axial direction. Step L2 represents the third stage and shows situated in the middle of these five steps. Step L1 is the fourth, the penultimate stage. Step L0 is the latest step and is the largest (in the radial direction). You have to understand that the five steps shown only as one example, the low pressure turbine may have more or less five steps.

Blade 20 action completed shank 40 lock, aerodynamic part 42 and the root part 44, passing between them. Aerodynamic part of 42 passes radially outwards from the root portion of 44 by the end part 46. Bandage 48 is designed as a single whole as part of a tail part of the 46 with a radius of 50 fillets, located in the middle part. As shown in figure 2, the bandage 48 is the first flat part 52, second flat portion of 54 and deepening 56, located in the lateral direction between the first flat part of the 52 and the second flat part 54. Deepening 56 below the first flat part 52 at the end of the first, where the first flat part and deepening 56 adjoin to each other. Deepening 56 raised up to the second flat part 54 on the other end, where a second flat part and deepening adjoin to each other. As shown in figure 2, the second planar part 54 elevated above the first flat part 52. In this design bandage 48 is at an angle relative to the end part 46, and the angle has values in the range of approximately 10 degrees to about 30 degrees, and the angle equal to 22.5 degrees is preferred. In the illustrative embodiment of the shank 40, aerodynamic part 42, root part 44, end part 46 and the band 48, are all manufactured as a single item of corrosion-resistant material, such as chrome-plated steel to the high strength. In the illustrative embodiment, the blade 20 annexed to the impeller 18 turbine (depicted in figure 1) through the shank 40 and passes in the radial direction from the outer impeller 18 turbines.

Figure 3 is an enlarged view of the axonometric shank 40 shown on the blade, shown in Figure 2 in accordance with one variant of execution of the present invention. In this embodiment, the shank 40 represents a shaft with a tilted axis entry with a bevel angle, equal to approximately 21 degree, which interacts with the dual slot limited in the working wheel of 18 turbines (see Figure 1). In one embodiment, the shank with sloping axial input has a design with three projections, which has six contact surfaces for interaction with the impeller 18 turbines (see Figure 1). Shank with sloping axial input is preferable to obtain the distribution medium and local mechanical stresses protection in conditions of high speed exceeding permissible, and adequate limits plastic fatigue (LCF), and also preferred for the root of the 44 aerodynamic parts. In addition, the Fig.z shown that the shank 40 has an axial width 43, which in one variant of execution can be in the range of approximately 3,87 inches (9,85 centimeters) to approximately 9,24 inches (23,64 inches), with a value equal to 3,87 inches (9,85 centimeters), is the preferred width. Shank 40 also has a groove 41 performed approximately 360 degrees, which holds the filler wire to maintain the axial position of the blades 20. The experts understand that the shank with sloping axial input may have more or fewer than the three tabs. Belonging to this right holder patent application in the United States with registration number 12/205,939 (case number GE 229084), entitled «SHANK WITH LOCK FOR the blade of a STEAM TURBINE AND impeller ROTOR», filed simultaneously with the present application, contains a more detailed discussion of the shaft castle.

In addition to providing more details on the shank 40, figure 3 also shows an enlarged view of the transition region, where shank 40 passes from the root portion of 44. In particular, figure 3 shows a radius 58 fillets in a place where the root of the 44 enters platform 60 shank 40.

Figure 5 presents a view of the axonometric, illustrating the relationship of adjacent bands 48 in accordance with one variant of execution of the present invention. Usually bandages 48 performed with a gap 68 of surfaces 64 between adjacent tyres and implement a contact by contact surfaces 66 during initial Assembly and/or under conditions of zero speed. In one embodiment, the gap 70 can be in the range of approximately - 0.002 inches (- 0,051 millimeter) up to approximately 0.008 inches (0,203 of a millimeter). Figure 5 shows that surface of 64 includes a part of the first flat part 52, second flat part 54 and deepening 56, whereas the contact surface of 66 includes a part of the second flat part 54. During work as the impeller rotation 18 turbine (shown in figure 1), the scapula 20 start to untwist. When the number of revolutions per minute (RPM) blades 20 approaching the operating level, the blades spin due to the centrifugal force, and the gaps in the contacting surfaces 66 are closed, and they are combined with each other so that there is estimated interaction with related tie-wraps. The result is that the blades form a single continuously interconnected design. In this design interconnected bandage provides enhanced rigidity of the shoulder blades, improved damping blades and improved seal on external radial parts of blades 20.

In the illustrative embodiment, the operating level for the blades of 20 is 3600 rpm, however, the specialists will be clear that the idea of the invention is equally applicable to the different scope of this settlement size. For example, a technician can change the scale of the work level of the proportionality factors, such as 1.2, 2 and 2.4 to get the blades which are, respectively, at 3000 rpm 1800 rpm and 1500 rpm.

Blade 20 in accordance with one variant of execution of the present invention preferably used in L2 stage part of the low-pressure steam turbine. However, the blade can also be used in other stages or in other parts (for example, high or medium pressure). As mentioned above, one preferred length for the scapula is approximately 20 10,56 inches (26,82 centimeters). The length of blades can provide output in a ring-shaped region L2 stage of approximately 20,09 square feet (1.87 m 2 ). This increased and improved output ring area can reduce the loss of kinetic energy, which is experiencing water vapor, when it leaves the blades L2 stage. This decrease in loss provides the increased efficiency of the turbine.

As noted above, the experts should understand that if the length of blades change in the scale of a different length, then it zooms will lead to the fact that the scale of output annular region will also change. For example, if it were using the coefficients of proportionality, such as 1.2, 2 and 2.4, to get the length of the blades, equal to, respectively, 12,67 inches (32,18 centimeters), 21,12 inches (53,64 centimeters) and 25,34 inches (64,36 centimeters), the output ring area would be equal to, respectively, approximately 28,93 square feet (2,69 m 2 ), 80,36 square feet (7,47 m 2 ), and 115,75 square feet (10,75 m 2 ).

Although the description of the invention is shown and described specifically in respect of the preferred embodiment of the invention, specialists should be clear that there may be changes and modifications. So we need to understand that the formula of the invention is intended to cover all such modifications and changes that are within the scope of the invention.

Parts List

10 Steam Turbine

12 Rotor 14 Shaft

18 Rotor Impeller

20 Blade

22 fixed Blades

24 Water Vapor

26 Inlet

30 Increased Side Pressure

32 Side Of Low Pressure

34 Front Edge

36 The Back Edge

38 Radial Length

40 Shank with castle

41 Groove

42 Aerodynamic Part

43 Axial Shank Width

44 the Root of the 46 end part

48 Bandage

50 Radius Galteli Between Tyre and End part

52 First Flat Part Of The Bandage

54 The Second Planar Part Of The Bandage

56 Deepening

58 Radius Galteli Between the Shank and the root part

60 Platform

62 the Place where the bandage is held by a given distance

from the front edge

64 Surface

66 Contact Surface

68 Gap

1. Blade (20) steam turbine containing: aerodynamic part (42), the root of (44)attached to one end of the aerodynamic parts (42), shank (40) with castle, passing from the root portion (44), and the shank (40) is shank (40) with sloping axial input, tail piece (46)attached to the aerodynamic parts (42) on the end opposite the root part (44), and the band (48), made in one piece as part of a tail part of the (46) with the first flat part (52), the second flat part (54) and deepening (56), located in the lateral direction between the first flat part (52) and the second flat part (54), the deepening of (56) is below the first flat part (52) at the end of the first, where the first flat part and deepening (56) adjacent to each other, and lifted up to the second flat part (54) on the other end, where a second flat part and deepening adjoin to each other, and a second flat part (54) elevated above the first flat part (52), and bandage (48) is located under a corner relative to the end part (46), which is in the range of approximately 10 degrees approximately 30 degrees.

2. Blade (20) according to claim 1, which has an output annular region, the area of which equals to about 20,09 square feet (1.87 m 2 ) or more.

3. Blade (20) according to claim 1, which has a working speed, component from approximately 1500 rpm to approximately 3600 rpm.

4. Blade (20) according to claim 1 in which the bandage (48) runs from places along a tail part, which is located at the specified distance from the front edge (34), the scapula (20), to the rear edge (36) blades (20).

5. Blade (20) according to claim 1 in which the bandage (48) has surface (64), which is made so that it is not in contact with adjacent tired roller blades (20) in stage steam turbine, and the contacting surface (66), which is made so that it is in contact with these tyres (48) blades (20), surface (64) includes the first part of the flat part (52), the second flat part (54) and deepening (56), and the contact surface (66) includes a part of the second flat part (54).

6. Part of the low-pressure steam turbine (10), containing: scapula (20) of the last stage in steam turbines, which are located around the impeller (18) turbine and each of them has: aerodynamic part (42), the length of which is approximately 10,56 inches (26,82 cm) or more, the root of (44)attached to one end of the aerodynamic parts (42), shank (40) with castle, passing from the root portion (44), and the shank (40) is a shank (40) with sloping axial input, tail piece (46)attached to the aerodynamic parts (42) on the end opposite the root part (44), and the band (48), made in one piece as part of a tail part (46) with the first flat part (52), the second flat part (54) and deepening (56), located in the lateral direction between the first flat part (52) and the second flat part (54), the deepening of (56) is below the first flat part (52) at the end of the first, where the first flat part and deepening (56) adjacent to each other, and lifted up to the second flat part (54) on the other end, where a second flat part and deepening adjoin to each other, and a second flat part (54) elevated above the first flat part (52), and bandage (48) is at an angle relative to the end part (46), which is in the range of approximately 10 degrees to about 30 degrees.

7. Part of low pressure 6, in which the indicated blades (20) have an output annular region, the area of which equals to about 20,09 square feet (1.87 m 2 ) or more.

8. Part of low pressure 6, in which the indicated blades (20) have a working speed, which is approximately from 1500 rpm to approximately 3600 rpm.

9. Part of low pressure 6, in which the bandages (48) these blades (20) collected settlement clearance (70) between them.

10. Part of low pressure on item 9, in which the estimated gap (70) is in the range of approximately - 0.002 inches (- 0,051 millimeter) up to approximately 0.008 inches (0,203 of a millimeter).