EP3351726A1

EP3351726A1 - Blade or vane for a compressor and compressor comprising said blade or vane

Info

Publication number: EP3351726A1
Application number: EP18152639.3A
Authority: EP
Inventors: Marco TAPPANI; Andrea Schneider
Original assignee: Ansaldo Energia SpA
Current assignee: Ansaldo Energia SpA
Priority date: 2017-01-19
Filing date: 2018-01-19
Publication date: 2018-07-25
Anticipated expiration: 2038-01-19
Also published as: EP3351726B1; CN108343637B; CN108343637A; IT201700005808A1

Abstract

A blade or vane for a compressor comprises a main body (15; 25) provided with a base face (16; 26), with a top face (17; 27), opposite with respect to the base face (16; 26), and with an outer face (18; 28), which extends between the base face (16; 26) and the top face (17; 27) and defines the airfoil profile of the blade or vane (7; 10; 70; 700); the main body (15; 25) being shaped so as to define along the outer face (18; 28) a leading edge (30), a trailing edge (31), a pressure side (32) and a suction side (33); and at least one appendix (29; 79; 779) arranged in the proximity of the trailing edge (31).

Description

PRIORITY CLAIM

This application claims priority from Italian Patent Application No. 102017000005808 filed on January 19, 2017 , the disclosure of which is incorporated by reference.
The invention relates to a blade or vane for a compressor and to a compressor comprising said blade or vane. In particular, the invention relates to a blade or vane for a compressor of a gas turbine power plant.
Gas turbine power plants usually comprise a compressor, where an air flow flows, a combustion chamber, which is supplied with a fuel and with air coming from the compressor, a gas turbine, where the gases coming from the combustion chamber flow, and a generator, which is mechanically connected to a common shaft of the gas turbine and of the compressor ad is connected to an electrical distribution network.
The compressor and the gas turbine extend along a longitudinal axis and respectively define a compression channel and an expansion channel, along which radial series of rotor blades, which rotate around the axis, alternate with radial series of stator vanes.
In the compressor, stall conditions can occur in the area of the aerofoil profile of the rotor blades or stator vanes. These conditions can cause instability phenomena, up to the surging of the entire compressor.
Since the surging of the compressor leads to a forced standstill of the plant and to the risk of serious structural damages for the compressor itself, the operation of the plant is usually limited so as to prevent this phenomenon from occurring. For example, the operation of the compressor can be restricted by limiting the value of the minimum air flow rate of the compressor to a safety value that exceeds the minimum values that can actually be borne by the compressor in order to ensure the operation thereof. This solution has evident negative impacts on the possibility of exploiting the potentialities of the plant.
Therefore, an object of the invention is to provide a blade or vane for a compressor, which is not affected by the drawbacks of the prior art; in particular, an object of the invention is to provide blade or vane for a compressor, which allows users to optimally and safely exploit the potentialities of the compressor in an easy and economic manner, both from the functional point of view and from the constructive point of view.
In accordance with these object, the invention relates to a blade or vane for a compressor comprising:

a main body provided with a base face, with a top face, opposite with respect to the base face, and with an outer face, which extends between the base face and the top face and defines the airfoil profile of the blade or vane; the main body being shaped so as to define along the outer face a leading edge, a trailing edge, a pressure side and a suction side;
at least one appendix arranged in the proximity of the trailing edge.

A further object of the invention is to provide a compressor, which is reliable and, at the dame time, efficient.
In accordance with these object, the invention relates to a compressor for a power plant as claimed in claim 16.
Further features and advantages of the invention will be best understood upon perusal of the following description of a non-limiting embodiment thereof, with reference to the accompanying drawing, wherein:

figure 1 is a schematic sectional view, with parts removed for greater clarity, of a power plant comprising the compressor according to the invention;
figure 2 is an enlarged view of a detail of the compressor of figure 1;
figure 3 is a schematic perspective view, with parts removed for greater clarity, of a detail of the blade or vane according to the invention;
figure 4 is a schematic view from the top, with parts removed for greater clarity, of the blade or vane of figure 3;
figure 5 is a sectional view along plane V-V indicated in figure 3;
figure 6 is a schematic perspective view, with parts removed for greater clarity, of a detail of the blade or vane according to the invention in accordance with a second embodiment;
figure 7 is a schematic perspective view, with parts removed for greater clarity, of a detail of the blade or vane according to the invention in accordance with a third embodiment;
figures 8A, 8B, 8C are schematic and simplified representations of the flow lines in the proximity of a compressor blade or vane according to the invention.

In figure 1, number 1 indicates a gas turbine power plant.
The plant 1 extends along a longitudinal axis A and comprises a combustion chamber 2, a stator 3 and a rotor 4, which rotates around the axis A.
The stator 3 comprises a stator casing 5, which extends around the axis A over the entire length of the rotor 4 and is static, a plurality of stator rings 6, which are centred on the axis A, are supported by the stator casing 5 and are arranged in succession along the axis A, and a plurality of stator vanes 7, which substantially extend along respective radial directions and are fixed to the stator casing 5 and to the respective stator rings 6.
The rotor 4 comprises a shaft 8 extending along the axis A, a plurality of rotor discs 9, which are coupled to one another so as to define one single element rotating around the axis A, and a plurality of rotor blades 10, which are divided into series and are arranged radially with respect to the axis A.
The stator rings 6 extend around the rotor discs 9 and are spaced apart from one another so that, along the axis A, radial series of rotor blades 10 alternate with radial series of stator vanes 7.
Said plurality of rotor discs 9, the stator rings 6 and the stator casing 5 define a compression channel 13a, where the air to be supplied in compression to the combustion chamber 2 flows, and an expansion channel 14a, where the hot gases coming from the combustion chamber 2 flow. The compression channel 13, the stator rings 6, the rotor discs 9 and the stator casing 5, which surround the compression channel 13, define the so-called compressor 13a.
The expansion channel 14, the stator rings 6, the rotor discs 9 and the stator casing 5, which surround the expansion channel 14, define the so-called turbine 14a.
The direction of the air flow is schematically shown by the arrow indicated with F.
Different stages follow one another along the compression channel 13. Each stage comprises a series of stator vanes 7 and a series of rotor blades 10.
Figure 2 schematically shows a portion of a stage of the compressor 13b, though without indicating in detail, for the sake of simplicity, all the aspects of the invention.
Each stator vane 7 of the compressor 13b comprises a main body 15, which is provided with a base face 16 coupled - in use - to the respective stator ring 6, with a top face 17 opposite the base face 16 and coupled - in use - to the stator casing 5, and with an outer face 18, which extends between the base face 16 and the top face 17 and defines the airfoil profile of the stator vane 7.
Basically, in use, the base face 16 is proximal to the axis A with respect to the top face 17 along the radial direction of extension of the stator vane 7.
Each rotor blade 10 of the compressor comprises a main body 25, which is provided with a base face 26 coupled - in use - to the respective rotor disc 9, with a top face 27, which is free and opposite the base face 26, and with an outer face 28, which extends between the base face 26 and the top face 27 and defines the airfoil profile of the rotor blade 10. The top face 27 is often defined "apex".
Basically, in use, the base face 26 is proximal to the axis A with respect to the top face 27 along the radial direction of extension of the rotor blade 10.
In figures 3, 4, 5, 6 we will refer, by mere way of example, to a stator vane 7 and to the respective main body 15.
Obviously, the features of the main body 15 and of the rotor vane 7 described here and hereinafter and shown in figures 3, 4 and 5 also apply to each rotor blade 10 of the compressor 13b and to the respective main body 25.
Figure 3 and figure 4 show a portion of the stator vane 7 according to the invention.
The vane 7 comprises the main body 15 described above and at least one appendix 29.
The main body 15, for the sake of simplicity, is represented like a solid body. However, the main body 15 can also be hollow.
More in detail, the main body 15 is shaped so as to define, along the outer face 18 a leading edge 30, a trailing edge 31, a pressure side 32 and a suction side 33.
The main body 15 has a radial height S (shown in figure 3), usually defined in the field as "span", an axial length C (shown in figure 4), usually defined in the field as "chord", and a median line M (shown with a broken line in figure 4), usually defined in the field as "camber line".
The appendix 29 is coupled to the main body 15 in the proximity of the trailing edge 31. In other words, the appendix 29 is arranged at a distance from the trailing edge 31 that is smaller than 20% of the axial length C.
In the non-limiting embodiment described and shown herein, the appendix 29 is arranged exactly in the area of the trailing edge 31 and, therefore, in this example the distance from the trailing edge 31 is substantially equal to zero.
Here and below, by appendix we mean a projection of the body, for example shaped like a wing, or a portion of the body itself, which is properly bent and/or shaped so as to obtain the specific aerodynamic effect described hereinafter.
In the non-limiting embodiment described and shown herein, the appendix 29 is arranged along the pressure side 32 in the proximity of the top face 17. In other words, the appendix 29 is arranged at a distance from the top face 17 that is smaller than 30% of the radial height S.
In the non-limiting embodiment described and shown herein, the appendix 29 is arranged exactly in the area of the top face 17 and, therefore, in this example the distance from the top face 17 is substantially equal to zero.
The appendix 29 extends along at least a portion of the trailing edge 31. Preferably, the appendix 29 has a radial height S1 that is equal to at least 2% of the radial height S of the main body 15.
In the non-limiting embodiment described and shown herein, the appendix 29 tapers towards the centre of the main body 15.
Figure 5 shows an axial section of the main body 15 in the area of plane V-V indicated in figure 3.
In the non-limiting embodiment described and shown herein, the appendix 29 has a substantially trapezoidal axial section.
In particular, the appendix 29 has a front face 40, a rear face 41 and an intermediate face 42 comprised between the rear face 41 and the front face 40. The position of the front face 40 and of the rear face 41 relates to the direction of the working fluid air flow in the compression channel 13. The front face 40, indeed, is the face that first meets the working fluid air flow in the compression channel 13.
In the non-limiting embodiment described and shown herein, the front face 40 is flat. According to a variant thereof, the front face is curved.
In the non-limiting example described and shown herein, the front face 40 projects from the pressure side 32 and is arranged so that the tangent in at least one point of the front face 40 intersects the median line M (camber line) forming an angle α that is greater than 10°, preferably greater than 30°.
In the example shown in figure 5, in which the front face 40 is flat, the tangent in at least one point of the front face 40 is the prolongation of the front face 40 itself.
In the non-limiting embodiment described and shown herein, the rear face 41 is flat. According to a variant thereof, the rear face is curved.
In the non-limiting example described and shown herein, the rear face 41 projects from the trailing edge 31 and is arranged so that the tangent in at least one point of the rear face 41 intersects the median line M (camber line) forming an angles β that is greater than 30°, preferably greater than 50°.
In the example shown in figure 5, in which the rear face 41 is flat, the tangent in at least one point of the rear face 41 is the prolongation of the rear face 41 itself.
The rear face has a width L, meaning the measure of the extension of the rear face 41 along a direction orthogonal to the median line M with respect to the pressure side 32, that is smaller than 10% of the axial length C (chord).
In the non-limiting example described and shown herein, the angle α is approximately 80° and the angles β is approximately 90°.
In the non-limiting embodiment described and shown herein, the intermediate face 42 is flat. According to a variant thereof, the intermediate face is curved.
Preferably, the main body 15 and the appendix 29 are manufactured as one single piece. In other words, the main body 15 and the appendix 29 are a one-piece body.
With reference to figure 8A, where the flow lines are schematically represented like broken lines, the appendix 29 is shaped so as to obtain a specific aerodynamic effect in the compression channel 13a, namely redistributing the working fluid flow rate on the blade or vane, moving the excess flow rate present on the central section of the main body 15 towards the end section of the main body 15 close to the top face 17. By so doing, stall is avoided even in operating conditions that would be impossible for traditional blades or vanes.
Figure 6 shows a stator vane 70 according to a second embodiment of the invention. In figure 6 the same reference numbers used in the preceding figures 3-5 can be found to indicate parts that are substantially identical or similar.
The vane 70 basically differs from the vane 7 because it comprises an appendix 79 that is arranged in the proximity of the base face 16, instead of in the proximity of the top face 17. In other words, the appendix 79 is arranged at a distance from the base face 16 that is smaller than 30% of the radial height S.
In the non-limiting embodiment described and shown herein, the appendix 79 is arranged exactly in the area of the base face 16 and, therefore, in this example the distance from the base face 16 is substantially equal to zero.
The appendix 79 has a radial height S2 that, again, is equal to at least 2% of the radial height S of the main body 15 and substantially has the same geometry as the appendix 29.
With reference to figure 8B, where the flow lines are schematically represented like broken lines, the appendix 79 is shaped so as to obtain a specific aerodynamic effect in the compression channel 13a, namely redistributing the working fluid flow rate on the blade or vane, moving the excess flow rate present on the central section of the main body 15 towards the end section of the main body 15 close to the base face 16. By so doing, stall can be avoided even in operating conditions that would be impossible for traditional blades or vanes.
Figure 7 shows a stator vane 700 according to a third embodiment of the invention. In figure 7 the same reference numbers used in the preceding figures 3-5 can be found to indicate parts that are substantially identical or similar.
The vane 700 basically differs from the vane 7 because it comprises a further appendix 779 that is arranged in the proximity of the base face 16.
In other words, the appendix 29 is arranged at a distance from the top face 17 that is smaller than 30% of the radial height S, whereas the appendix 779 is arranged at a distance from the base face 16 that is smaller than 30% of the radial height S.
In the non-limiting example described and shown herein, the appendix 29 is arranged exactly in the area of the top face 17 and, therefore, in this example the distance from the top face 17 is substantially equal to zero, and the appendix 779 is arranged exactly in the area of the base face 16 and, therefore, in this example the distance of the appendix 779 from the base face 16 is substantially equal to zero.
The appendix 779 has a radial height S2 that, again, is equal to at least 2% of the radial height S of the main body 15 and substantially has the same geometry as the appendix 29.
According to a variant that is not shown herein, the appendix 29 and the appendix 779 have different geometries, so as to determine different and targeted flow deflecting effects.
With reference to figure 8C, where the flow lines are schematically represented like broken lines, the appendices 29 and 779 are shaped so as to obtain a specific aerodynamic effect in the compression channel 13a, namely redistributing the working fluid flow rate on the blade or vane, moving the excess flow rate present on the central section of the main body 15 towards the end sections of the main body 15 close to the top face 17 and to the base face 16. By so doing, stall can be avoided even in operating conditions that would be impossible for traditional blades or vanes.
As already mentioned above, the features of the vane 7, 70, 700 described with reference to figures 4 to 7 can also be applied to the rotor blades 10.
The blades or vanes 7, 10, 70, 700 according to the invention are capable of significantly increasing the flow deflection capacity in the proximity of one end or both ends of the main body 15, 25. By so doing, stall can be avoided even in operating conditions that would be impossible for traditional blades or vanes. As already mentioned above with reference to figures 8A, 8B, 8C, the appendices 29, 79, 779 are capable of redistributing the working fluid flow rate on the blade or vane 7, 10, 70, 700, moving the excess flow rate present on the central section towards one or more end sections of the main body 15, 25.
As a matter of fact, the risk of stall increases in the area of the ends. The airfoil profiles of the blades or vanes of a compressor operate in different conditions in the central portion of the profile and at the two radial ends. In the aforesaid end areas, the blades or vanes cannot generate a deflection of the flow that is sufficient to make sure that the flow adheres to the profile, hence the function of the entire blade or vane is jeopardized.
The adherence of the flow to the profile of a blade or vane, or the lack thereof, depends on the shape of the blade or vane profile, on the speed of the flow and on the presence of viscous frictions, vortices and other disturbing aerodynamic phenomena.
In the end areas of a blade or vane viscous losses are high. When working fluid flow rates are low (for example, when the plant is operated with a minimum load), the end areas are the ones that are most subjected to flow separation and, therefore, to stall risk.
Thanks to this invention, therefore, the tendency to stall is reduced in the end sections of the blade or vane 7, 10, 70, 700 and, as a consequence, the useful operating range of the compressor 13b is increased, with evident advantages in terms of performances of the entire plant 1.
Advantageously, in the blades or vanes 7, 10, 70, 700 according to the invention, the airfoil profile (i.e. the outer face 18, 28 of the main body 15, 25) is not changed in terms of curvature, axial or radial dimensions.
This avoids expensive and complicated interventions from the designing and constructive point of view.
The simple addition of one or more appendices determined an increase in the capacity of the blade or vane of redistributing the flow rate from the central section to the end one, given the same surface. This is determined by a significant increase in the lift of the end sections, though with a low resistance increase.
As a matter of fact, where there is an appendix, the blade or vane acts as if its axial length (chord) were longer. Estimations indicate that the appendix generates a blade or vane lift that is similar to the one of a blade or vane that has a surface increased by 20%.
In conclusion, thanks to the blade or vane according to the invention, the operating field of the compressor 13b is widened without important structural interventions.
The reduced dimensions of the appendices 29, 79 779 make this invention easy and cheap to be manufactured.
Finally, it is clear that the blade or vane and the compressor described herein can be subjected to changes and variations, without for this reason going beyond the scope of protection set forth in the appended claims.

Claims

Blade or vane for a compressor comprising:
- a main body (15; 25) provided with a base face (16; 26), with a top face (17; 27), opposite with respect to the base face (16; 26), and with an outer face (18; 28), which extends between the base face (16; 26) and the top face (17; 27) and defines the airfoil profile of the blade or vane (7; 10; 70; 700); the main body (15; 25) being shaped so as to define along the outer face (18; 28) a leading edge (30), a trailing edge (31), a pressure side (32) and a suction side (33);

- at least one appendix (29; 79; 779) arranged in the proximity of the trailing edge (31).
Blade or vane according to claim 1, arranged, in use, along a radial direction with respect to the extension axis (A) of the compressor (13b); the main body (15; 25) having a radial height (S) and an axial length (C).
Blade or vane according to any one of the foregoing claims, wherein the appendix (29; 79; 779) is arranged along the pressure side (32).
Blade or vane according to any one of the foregoing claims, wherein the appendix (29; 79; 779) extends along at least one portion of the trailing edge (31).
Blade or vane according to any one of the foregoing claims, wherein the appendix (79; 779) is arranged in the proximity of the base face (16; 26).
Blade or vane according to any one of the foregoing claims, wherein the appendix (29) is arranged in the proximity of the top face (17; 27).
Blade or vane according to any one of the foregoing claims, wherein the appendix (29; 79; 779) tapers towards the centre of the main body (15; 25).
Blade or vane according to any one of claims from 2 to 7, wherein the appendix (29; 79; 779) has a radial height (S1; S2; S1, S2) equal to at least 2% of the radial height (S) of the main body.
Blade or vane according to any one of claims from 2 to 8, wherein the appendix (29; 79; 779) has a substantially trapezoidal axial section.
Blade or vane according to any one of claims from 2 to 9, wherein the appendix (29; 79; 779) presents a front face (40), a rear face (41) and an intermediate face (42) comprised between the rear face (41) and the front face (40).
Blade or vane according to claim 10, wherein the front face (40) is arranged so that the tangent in at least one point of the front face (40) intersects a median line (M) forming a first angle (α) greater than 10°, preferably greater than 30°.
Blade or vane according to claim 10 or 11, wherein the rear face (41) is arranged so that the tangent in at least one point of the rear face (41) intersects a median line (M) forming a second angle (β) greater than 30°, preferably greater than 50°.
Blade or vane according to any one of claims from 10 to 12, wherein the rear face (41) has a width (L), intended as the measure of the extension of the rear face (41) along a direction orthogonal to the median line (M) with respect to the pressure side (32), smaller than 10% of the axial length (C).
Blade or vane according to claim 5, comprising a further appendix (29) extending along a further portion of the trailing edge (31) in the proximity of the top face (17).
Compressor for a gas turbine power plant extending along a longitudinal axis (A) and provided with a plurality of rotor blades (10) and with a plurality of stator vanes (7); at least one of the plurality of rotor blades (10) and of the plurality of stator vanes (7) being of the type claimed in anyone of the foregoing claims.