CN212079396U - Element-level tenon type turbine blade with front edge provided with five pressure sensing holes - Google Patents
Element-level tenon type turbine blade with front edge provided with five pressure sensing holes Download PDFInfo
- Publication number
- CN212079396U CN212079396U CN202020092157.2U CN202020092157U CN212079396U CN 212079396 U CN212079396 U CN 212079396U CN 202020092157 U CN202020092157 U CN 202020092157U CN 212079396 U CN212079396 U CN 212079396U
- Authority
- CN
- China
- Prior art keywords
- pressure
- blade
- pressure sensing
- sensing hole
- holes
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
- 238000013461 design Methods 0.000 claims description 12
- 238000009434 installation Methods 0.000 claims description 4
- 239000000523 sample Substances 0.000 abstract description 21
- 230000003068 static effect Effects 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 4
- 238000005259 measurement Methods 0.000 description 13
- 238000012360 testing method Methods 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000001939 inductive effect Effects 0.000 description 3
- 238000004080 punching Methods 0.000 description 3
- 238000012938 design process Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 210000001520 comb Anatomy 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000004599 local-density approximation Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000000917 particle-image velocimetry Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a tenon type turbine blade with five pressure sensing holes on a primitive-level front edge. Comprises a pressure sensing hole, a pressure guide channel, a blade top tenon, a blade root tenon, a low-loss bent pipe and a pressure guide pipe interface. A plurality of rows of pressure sensing holes are distributed on the front edge of the blade along the height of the blade, and each row comprises five pressure sensing holes; the pressure guide channel is respectively connected with the orifice of the pressure sensing hole and the pressure guide pipe interface. The method can simultaneously measure the total pressure, the static pressure, the deflection angle and the Mach number of the air flow in the range of +/-120 degrees of included angle between the incoming flow direction and the front edge at the positions of the turbine inlet and the rotor outlet along the blade height direction, a plurality of element stages, and is suitable for measuring the distribution of two-dimensional flow field parameters of the rotor outlet along the blade height direction under various working conditions. The invention not only has the aerodynamic performance and strength of the conventional turbine blade, but also has the function of measuring flow field parameters, compared with the conventional pressure probe and blade type probe measuring technology, the invention has no overhanging probe, does not interfere the measured flow field, does not influence the aerodynamic performance of the blade, and has high parameter measuring precision.
Description
Technical Field
The invention belongs to the field of power machinery, relates to a turbine, and particularly relates to a tenon type turbine blade with five pressure sensing holes on a front edge of a cell level.
Background
There are several ways of mounting turbine stator blades to a casing, one of the more common mounting being a circumferential tongue and groove connection. The blade is characterized in that tenons are respectively arranged at the blade top and the blade root of the blade, the blade can slide into circumferential mortises on a casing and a hub along the circumferential direction through the tenons, and then the blade is fixed by using locking plates or rivets. The mounting mode can avoid the situation that holes are formed in the casing, and meanwhile, due to the fact that a large gap exists between the blade top tenon and the mortise, cooling air can be introduced into the gap to cool the blade.
In the turbine, the blades of the turbine are cut by a cylindrical surface coaxial with the turbine, and the section of the turbine blade is called the elementary stage of the blade.
In the current turbine blade aerodynamic design process, the velocity triangle of the inlet and the outlet of the turbine is determined firstly. The velocity triangle mainly includes four parameters: axial speed, prerotation, circumferential speed and torsional speed. Wherein the axial velocity is determined by the flow through the turbine. The circumferential speed and torque are determined by the rim work. The inlet angle and the outlet angle of the element level can be obtained through calculation of the inlet and outlet speed triangles, different attack angles are given for the element levels at different positions, and the installation angle corresponding to each element level can be obtained by combining the drop angle, the front edge angle and the rear edge angle of the blade. And then stacking the obtained primitive levels to obtain the three-dimensional shape of the blade body.
In addition to the dynamic design and the structural design, the strength design of the turbine blade is also needed to ensure the sufficient strength of the blade. The design process of the blade is therefore a multi-parameter optimization design that requires iterative iterations. On the premise of ensuring that the turbine blades have sufficient strength, designers also want the blades to be as light as possible, which is beneficial to reducing the overall weight of the aircraft engine or gas turbine, and improving the thrust-weight ratio of the aircraft engine or the efficiency of the gas turbine.
The internal flow of the turbine presents complex strong three-dimension and unsteady property, the structure and the profile of the blade are complex, and the axial space between a rotor and a stator is very narrow. In addition, the working medium in the turbine is high-temperature high-pressure fuel gas discharged by the combustion chamber. Due to these problems, conventional testing approaches are often limited.
Contact measurement devices such as pressure probes, including pressure probe combs and leaf probes, which allow simultaneous measurements at multiple points, are most commonly provided with a forwardly extending probe head. The pressure probe comb is limited by the size of the pressure probe comb, cannot be inserted into a narrow flow channel between small-sized blade rows to carry out interstage flow field parameter testing, and even if the pressure probe comb can be inserted, a probe head and a support rod can cause great interference on a measured flow field. More importantly, the pressure probe or the pressure probe comb can be inserted into the flow field between the rotor and the stator only by punching a hole in the casing, and for the turbine, the rotor and the stator often have a double-layer casing therebetween as shown in fig. 15, so that the punching process on the casing is difficult. The punching also destroys the integrity of the casing mechanism and has the possibility of air leakage, further disturbing the original flow field structure.
The blade-shaped probe can be inserted into a narrow flow channel between small-sized blade rows to carry out interstage flow field parameter testing, but can generate great interference on a measured flow field, particularly a flow field near the wall surface of a blade, damage the original structure of the flow field, cause larger measurement errors, and even bring extra flow loss so as to deteriorate the original pneumatic load of the blade and the working capacity of a turbine.
Secondly, three-hole pressure probes are mostly adopted for measuring two-dimensional flow field parameters, but the air flow angle range which can be measured by the existing and better three-hole pressure probes is only +/-40 degrees. The change of the air flow angle in the turbine is severe along with the change of the working state of the turbine, and the air flow angle change range can reach +/-60 degrees to +/-70 degrees under some working conditions, so that the existing three-hole pressure probe cannot accurately measure the two-dimensional flow field parameters in the turbine.
The hot wire anemometer is also one of the commonly used testing means for the flow field in the turbine, but the hot wire is easy to break and is easy to be polluted by impurities, so that the measuring result is inaccurate.
Although the flow field structure cannot be damaged by non-contact measurement means such as a particle image velocity measurement technology and a laser Doppler velocity measurement technology, the flow field of a blade root region cannot be measured due to the fact that a complex profile of the blade shields laser or a narrow flow channel shields laser, and in addition, the laser irradiates a wall surface and generates strong reflection light to cause measurement errors. Particle following problems can also lead to large measurement errors. The particle image velocimetry technology and the laser Doppler velocimetry technology can only measure speed and cannot measure pressure, and the pressure data is more concerned in the turbine performance experiment.
The existing turbine blade design does not include an inter-stage aerodynamic parameter measurement design, so that accurate inter-stage flow field parameter testing cannot be carried out in narrow flow channels among small-size turbine blade rows.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the tenon type turbine blade with the element-level front edge provided with the five pressure sensing holes is invented to solve the technical problem that accurate measurement of interstage flow field parameters cannot be carried out in a narrow flow channel between small-sized turbine blade rows.
The technical solution of the invention is as follows:
a cellular-grade turbine blade having a leading edge with five pressure sensing holes, comprising: the blade comprises a blade pressure surface (1), a blade suction surface (2), a pressure surface rear pressure sensing hole (3), a pressure surface front pressure sensing hole (4), a leading edge point pressure sensing hole (5), a suction surface front pressure sensing hole (6), a suction surface rear pressure sensing hole (7), a pressure guide channel (8), a low-loss bent pipe (9), a blade top tenon (10), a blade root tenon (11) and a pressure guide pipe interface (12); the blade front edge is provided with a plurality of rows of pressure sensing holes along the blade height direction, each row comprises 5 pressure sensing holes positioned on the surface of the blade, namely a front edge point pressure sensing hole (5) positioned at the front edge point of the blade, a suction surface front pressure sensing hole (6) positioned on the suction surface of the blade (2), a suction surface rear pressure sensing hole (7), a pressure surface rear pressure sensing hole (3) positioned on the pressure surface of the blade (1) and a pressure surface front pressure sensing hole (4), the central lines of the five holes are positioned on the same blade element level, and the diameters of the pressure sensing holes are 0.2mm to 1 mm; the central line of the pressure sensing hole (5) at the front edge point is superposed with the tangent line of the camber line of the primitive level where the central line is positioned at the front edge point; press and pressThe center lines of the pressure sensing holes (3) behind the force surface and the suction surface (7) are collinear, and are normals of 0.5 to 20 percent of the length points of the element-level middle arcs from the element-level front edge points; the central line of the front pressure sensing hole (4) of the pressure surface forms an included angle of 30-45 degrees with the central line of the rear pressure sensing hole (3) of the pressure surface and the central line of the rear pressure sensing hole (7) of the suction surface, and the central line of the front pressure sensing hole (6) of the suction surface forms an included angle of 30-45 degrees with the central lines of the rear pressure sensing hole (3) of the pressure surface and the rear pressure sensing hole (7) of the suction surface; one end of the pressure guide channel (8) is connected with the orifice of the pressure sensing hole, and the other end is connected with a pressure guide pipe interface (12) positioned in the blade top tenon (10); the diameter of the pressure guide channel is consistent with that of the pressure sensing hole and ranges from 0.2mm to 1 mm; on the primitive level where the center line of the pressure sensing hole is located, the center line of a pressure guide channel (8) connected with the pressure sensing hole (5) at the leading edge point is superposed with the camber line of the primitive level of the blade, the center lines of the other pressure guide channels (8) are all equal distance lines of the center line of the pressure guide channel (8) connected with the pressure sensing hole (5) at the leading edge point, all the pressure guide channels (8) extend towards the rear of the blade at the primitive level where the pressure guide channels are located, and are bent towards the direction of a blade top tenon (10) at the chord length of 30-70% of the length from the leading edge point of the blade, and a low-loss bent pipe (9) is adopted at; the central line of the low-loss bent pipe (9) is a polar coordinate curve rho2＝a2sin2 theta, wherein a is 1 to 4 times the diameter of the pressure leading channel (8), and the curve section of the curve theta with the value between 0 and 30 degrees is the central line of the low-loss elbow (9) and is tangent with the central lines of the two connected pressure leading channels (8); the bent pressure guide channel (8) adopts a straight channel design; the center line of the pressure guide pipe interface (12) and the center line of the tail end of the pressure guide channel (8) form an included angle of 30-45 degrees, the length is 2-20 mm, and the diameter is 0.4-2 mm; after the pressure guiding pipe is connected to the pressure guiding pipe interface (12), the pressure guiding pipe can be arranged through a circumferential gap between the blade top tenon (10) and the casing installation guide rail and finally led out from an opening on the casing;
a cellular-grade turbine blade having a leading edge with five pressure sensing holes, comprising: the invention has a plurality of rows of pressure sensing holes; the row closest to the blade root is 0.2 to 1mm away from the blade root; the row closest to the leaf top is 0.2 to 1mm away from the leaf top; and in the range of 25% of the blade height close to the blade root or close to the blade top, the distance between two adjacent rows of pressure sensing holes is 5% to 15% of the blade height, and the distance between two adjacent rows of pressure sensing holes at the rest blade heights is 10% to 20% of the blade height.
The pressure sensed by the pressure sensing hole is transmitted to the pressure sensor through the pressure guiding channel and the pressure guiding pipe; the pressure sensor converts the pressure signal into an electric signal to be output, and the electric signal output by the pressure sensor can be converted into a pressure value measured by the pressure sensing hole through the computer data acquisition and processing system; the tenon type turbine blade with the five pressure sensing holes on the element-level front edge can be calibrated in a calibration wind tunnel, pressure values of the five pressure sensing holes on each element level under the conditions of different incoming flow Mach numbers and different incoming flow deflection angles are obtained, and a total pressure coefficient, a static pressure coefficient, an airflow deflection angle coefficient and the like are calculated by combining known incoming flow total pressures and static pressures; after the tenon type turbine blade with the five pressure sensing holes on the element-level front edge is installed on a turbine, pressure sensed by the five pressure sensing holes on each element can be obtained in actual work, and the total pressure coefficient, the static pressure coefficient and the airflow deflection angle coefficient obtained on a calibration wind tunnel are utilized to obtain the data of the total pressure, the static pressure, the Mach number and the airflow deflection angle of actual incoming flow; because the invention has a plurality of rows of pressure sensing holes, the invention can simultaneously measure the two-dimensional flow field parameter distribution of the turbine inlet and the rotor outlet at a plurality of blade element level positions along the blade height direction.
The invention has the beneficial effects that:
the pressure guide channels are relatively large in distance and reasonable in distribution, the strength of the blade cannot be adversely affected, the pressure guide channels are low-loss bent pipes, pressure loss can be effectively reduced, stress concentration can be avoided, and the weight of the blade can be reduced. The invention not only has the aerodynamic performance and strength of the conventional blade, but also has the function of simultaneously measuring two-dimensional flow field parameters of a plurality of blade element level positions along the blade height direction; the two-dimensional flow field parameters can be measured without inserting a pressure probe, and an overhanging probe is not needed, so that the flow field structure is not damaged, the pneumatic performance of the blade is not deteriorated, and an additional measurement error is not introduced; compared with a blade-type probe, the non-overhanging probe means that the weight of the invention is lighter, which is beneficial to reducing the whole weight of a turbine test piece; the pressure sensing hole close to the blade root can be arranged very close to the blade root, and the pressure sensing hole close to the blade top can also be arranged very close to the blade top, so that the measurement resolution of the blade root and the blade top is improved; meanwhile, each element stage provided with the pressure sensing holes is provided with five pressure sensing holes, so that two-dimensional flow field parameters such as total pressure, static pressure, Mach number, deflection angle of airflow and the like in the range of +/-120 degrees of included angle between the incoming flow direction and the front edge can be measured; compared with the existing blade, the invention fully considers the aerodynamic design, the structure, the strength and the weight design of the blade, creatively provides the position and the size of the pressure sensing hole, the design and the layout of the pressure guide channel and the like, and has outstanding characteristics and substantial progress in the aspects of the design of the turbine blade and the aerodynamic experimental measurement.
Drawings
FIG. 1 is an isometric view of a dovetail turbine blade with five pressure sensing holes from a primitive-level leading edge of the present invention.
Fig. 2 is a left side view of fig. 1.
Fig. 3 is a front view of fig. 1.
Fig. 4 is a right side view of fig. 1, partially in section.
FIG. 5 is a primitive level of FIG. 1 showing the mean camber line of the blade primitive level and the relative positions of the five pressure sensing hole aperture centerlines on the primitive level.
Fig. 6 is a cross-sectional view of fig. 1, where the run of the channels in the cell level can be seen.
Fig. 7 is a perspective view of fig. 1.
Fig. 8 is a schematic view of the installation of fig. 1.
FIG. 9 is an isometric view of a second exemplary dovetail turbine blade embodiment with five pressure sensing holes in the leading edge of the primitive stage of the present invention.
Fig. 10 is a left side view of fig. 9.
Fig. 11 is a front view of fig. 9.
Fig. 12 is a right side view of fig. 9, partially in section.
Fig. 13 is a cross-sectional view of fig. 9, where the run of the channels in the cell level can be seen.
Fig. 14 is a low loss elbow centerline definition.
FIG. 15 is a schematic view of the turbine rotor exit configuration.
Wherein: 1-blade pressure surface, 2-blade suction surface, 3-pressure surface rear pressure sensing hole, 4-pressure surface front pressure sensing hole, 5-leading edge point pressure sensing hole, 6-suction surface front pressure sensing hole, 7-suction surface rear pressure sensing hole, 8-pressure guide channel, 9-low-loss bent pipe, 10-blade tip tenon, 11-blade root tenon, 12-pressure guide pipe interface, 13-primitive stage leading edge point, 14-primitive stage middle arc line length point starting from primitive stage leading edge point 5%, 15-primitive stage middle arc line, 16-primitive stage trailing edge point, 17-turbine rotor blade, 18-turbine rotor outlet double-layer casing, 19-turbine stator blade, 20-opening hole on the casing, 21-clearance between casing and tenon.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
Example one
As shown in FIGS. 1, 2 and 3, the present embodiment describes a dovetail turbine blade with five pressure sensing holes in the leading edge; the blade contains blade pressure surface (1), blade suction surface (2), pressure surface rear pressure-sensitive receiving hole (3), pressure surface front pressure-sensitive receiving hole (4), leading edge point pressure-sensitive receiving hole (5), pressure-sensitive receiving hole (6) before the suction surface, pressure-sensitive receiving hole (7) behind the suction surface, induced pressure passageway (8), low return bend (9), blade top tenon (10), blade root tenon (11), induced pressure pipe interface (12). The blade is provided with five rows of pressure sensing holes distributed along the blade height direction, each row comprises a front edge point pressure sensing hole (5) located at an elementary-level front edge point, a pressure surface rear pressure sensing hole (3) and a pressure surface front pressure sensing hole (4) located on a blade pressure surface (1), and a suction surface front pressure sensing hole (6) and a suction surface rear pressure sensing hole (7) located on a blade suction surface (2). The pressure sensing hole center line of each row is on the same elementary level, and the diameter of each hole is 1 mm. The distance from the first row of pressure sensing holes to the blade root is 1mm from the blade root, the distance from the second row of pressure sensing holes to the blade root is 25% of the blade height, the distance from the third row of pressure sensing holes to the blade height is 50% of the blade height, the distance from the fourth row of pressure sensing holes to the blade height is 75% of the blade height, and the distance from the fifth row of pressure sensing holes to the blade top is 1 mm; the pressure guide channel (8) is a passage inside the blade, and the diameter of the pressure guide channel is 1mm which is the same as that of the pressure sensing hole; one end of the pressure guide channel is connected with the orifice of the pressure sensing hole, the other end of the pressure guide channel is connected with a pressure guide pipe interface (12), the length of the pressure guide pipe interface is 20mm, and the diameter of the pressure guide pipe interface is 2 mm.
FIG. 4 shows the orientation of the pressure guiding channel (8) inside the blade and the relative position of the pressure guiding pipe joint (12) on the blade tip tenon (10); one end of the pressure guide channel (8) is connected with the orifice of the pressure sensing hole and extends to the tail edge of the blade, and the pressure guide channel is bent towards the upper part of the blade at a certain chord length position, and the bent part is a low-loss bent pipe; referring to fig. 14, the low loss elbow centerline is a polar curve ρ2＝a2A portion sin2 theta, the solid line portion in the figure, where a has a value of twice the diameter of the impulse channel; and taking the curve section of the curve theta value between 0 and 30 degrees as the central line of the low-loss bent pipe, and respectively tangent with the central lines of the two connected pressure guide channels (8). The bent pressure guide channel (8) is connected with a pressure guide pipe interface (12) in the blade top tenon (10), and the included angle between the central line of the pressure guide pipe interface (12) and the central line of the pressure guide channel (8) is 45 degrees.
FIG. 5 is a primitive level of the blade with the leading edge point pressure sensing hole (5) centerline coincident with the tangent of the primitive level camber line (15) at the leading edge point (13); the orifice of the suction surface rear pressure sensing hole (7) and the orifice of the pressure surface rear pressure sensing hole (3) share a central line, and the central line is a normal line of a mean camber line passing through a 5% length point (14) of a mean camber line of the primitive level from a front edge point of the primitive level; the central lines of the orifice of the front pressure sensing hole (6) of the suction surface and the orifice of the front pressure sensing hole (4) of the pressure surface form an included angle of 45 degrees with the central lines of the orifice of the rear pressure sensing hole (7) of the suction surface and the orifice of the rear pressure sensing hole (3) of the pressure surface.
FIG. 6 is a primitive level of a blade with pressure sensing holes, the center lines of the pressure inducing channels (8) connecting the orifices of the pressure sensing holes (5) at the leading edge point are coincident with the camber line of the blade and extend towards the trailing edge of the blade, and the center lines of the rest pressure inducing channels (8) are all equidistant lines connecting the center lines of the pressure inducing channels (8) of the pressure sensing holes (5) at the leading edge point and extend towards the trailing edge of the blade; the first row of pressure sensing holes from the blade root to the blade top are bent upwards from the 70% chord length from the primitive level front edge point, the bent part is a low-loss bent pipe (9), the bent pressure guide channel (8) is a straight pipeline and is finally connected with a pressure guide pipe interface (12) in a blade top tenon (10); the second row of pressure sensing holes from the blade root to the blade top are bent to the upper part of the blade at the chord length of 60 percent from the front edge point of the primitive level, the bent part is a low-loss bent pipe (9), the bent pressure guide channel (8) is a straight pipeline and is finally connected with a pressure guide pipe interface (12) in a blade top tenon (10); the third row of pressure sensing holes from the blade root to the blade top are bent towards the upper part of the blade at the chord length of 50 percent from the front edge point of the primitive level, the bent part is a low-loss bent pipe (9), the bent pressure guide channel (8) is a straight pipeline and is finally connected with a pressure guide pipe interface (12) in a blade top tenon (10); the fourth row of pressure sensing holes from the blade root to the blade top are bent to the upper part of the blade at the chord length of 40 percent from the front edge point of the primitive level, the bent part is a low-loss bent pipe (9), the bent pressure guide channel (8) is a straight pipeline and is finally connected with a pressure guide pipe interface (12) in a blade top tenon (10); and the pressure sensing holes in the fifth row from the blade root to the blade top are bent upwards from the chord length of 30% of the front edge point of the primitive stage, the bent part is a low-loss bent pipe (9), the bent pressure guide channel (8) is a straight pipeline, and finally the pressure guide channel is connected with a pressure guide pipe interface (12) in a blade top tenon (10).
FIG. 8 illustrates a method of mounting the present invention to a turbine casing. The turbine casing and the hub are respectively provided with a mortise along the circumferential direction, and the blade top tenon is slid into the mortise; the pressure pipe is connected to a pressure pipe interface (12) in the tip tenon (10) and exits through a circumferential gap between the tip tenon and the casing mounting rail and an opening in the casing surface.
Example two
9, 10 and 11, the present embodiment describes a dovetail turbine blade with a leading edge with five pressure sensing holes; the blade contains blade pressure surface (1), blade suction surface (2), pressure surface rear pressure-sensitive receiving hole (3), pressure surface front pressure-sensitive receiving hole (4), leading edge point pressure-sensitive receiving hole (5), pressure-sensitive receiving hole (6) before the suction surface, pressure-sensitive receiving hole (7) behind the suction surface, induced pressure passageway (8), low return bend (9), blade top tenon (10), blade root tenon (11), induced pressure pipe interface (12). The blade is provided with three rows of pressure sensing holes distributed along the blade height direction, each row comprises a front edge point pressure sensing hole (5) positioned at a front edge point, a pressure surface rear pressure sensing hole (3) and a pressure surface front pressure sensing hole (4) positioned on a blade pressure surface (1), and a suction surface front pressure sensing hole (6) and a suction surface rear pressure sensing hole (7) positioned on a blade suction surface (2). The pressure-sensing hole center line of each row is on the same primitive level, and the diameter of each hole is 0.2 mm. The distance from the first row of pressure sensing holes to the blade root is 1mm from the blade root direction, the distance from the second row of pressure sensing holes to the blade top is 1mm, the distance from the third row of pressure sensing holes to the blade root is 50% of the blade height; the pressure guide channel (8) is a passage inside the blade, and the diameter of the pressure guide channel is 0.2mm which is the same as that of the pressure sensing hole; one end of the pressure guide channel is connected with the orifice of the pressure sensing hole, the other end of the pressure guide channel is connected with a pressure guide pipe interface (12), the length of the pressure guide pipe interface is 4mm, and the diameter of the pressure guide pipe interface is 0.4 mm.
FIG. 12 shows the orientation of the rail passage (8) within the bucket and the relative position of the rail connection (12) on the bucket tip (10); one end of the pressure guide channel (8) is connected with the orifice of the pressure sensing hole and extends to the tail edge of the blade, and the pressure guide channel is bent towards the upper part of the blade at a certain chord length position, and the bent part is a low-loss bent pipe; referring to fig. 14, the low loss elbow centerline is a polar curve ρ2＝a2A portion sin2 theta, the solid line portion in the figure, where a has a value of twice the diameter of the impulse channel; and taking the curve section of the curve theta value between 0 and 30 degrees as the central line of the low-loss bent pipe, wherein the curve section is respectively tangent to the central lines of the two connected pressure leading channels. The bent pressure guide channel (8) is connected with a pressure guide pipe interface (12) in the blade top tenon (10), and the included angle between the central line of the pressure guide pipe interface (12) and the central line of the pressure guide channel (8) is 45 degrees.
FIG. 5 is a primitive level of the blade with the leading edge point pressure sensing hole (5) centerline coincident with the tangent of the primitive level camber line (15) at the leading edge point (13); the orifice of the suction surface rear pressure sensing hole (7) and the orifice of the pressure surface rear pressure sensing hole (3) share a central line, and the central line is a normal line of a mean camber line passing through a 5% length point (14) of a mean camber line of the primitive level from a front edge point of the primitive level; the central lines of the orifice of the front pressure sensing hole (6) of the suction surface and the orifice of the front pressure sensing hole (4) of the pressure surface form an included angle of 45 degrees with the central lines of the orifice of the rear pressure sensing hole (7) of the suction surface and the orifice of the rear pressure sensing hole (3) of the pressure surface.
FIG. 13 is a primitive level of a blade with pressure sensing holes, the center line of the pressure guiding channel (8) connecting the orifices of the pressure sensing holes (5) at the leading edge point coincides with the camber line of the blade and extends towards the trailing edge of the blade, and the center lines of the rest pressure guiding channels (8) coincide with the center line of the pressure guiding channel (8) connecting the pressure sensing holes (5) at the leading edge point and extend towards the trailing edge of the blade; the first row of pressure sensing holes from the blade root to the blade top are bent upwards from the 70% chord length from the primitive level front edge point, the bent part is a low-loss bent pipe (9), the bent pressure guide channel (8) is a straight pipeline and is finally connected with a pressure guide pipe interface (12) in a blade top tenon (10); the second row of pressure sensing holes from the blade root to the blade top are bent towards the upper part of the blade at the chord length of 50 percent from the front edge point of the primitive level, the bent part is a low-loss bent pipe (9), the bent pressure guide channel (8) is a straight pipeline and is finally connected with a pressure guide pipe interface (12) in a blade top tenon (10); and the third row of pressure sensing holes from the blade root to the blade top are bent upwards from the 30 percent chord length from the front edge point of the primitive level, the bent part is a low-loss bent pipe (9), the bent pressure guide channel (8) is a straight pipeline, and finally the pressure guide channel is connected with a pressure guide pipe interface (12) in the blade top tenon (10).
FIG. 8 illustrates a method of mounting the present invention to a turbine casing. The turbine casing and the hub are respectively provided with a mortise along the circumferential direction, and the blade top tenon is slid into the mortise; the pressure pipe is connected to a pressure pipe interface (12) in the tip tenon (10) and exits through a circumferential gap between the tip tenon and the casing mounting rail and an opening in the casing surface.
Claims (1)
1. A cellular-grade turbine blade having a leading edge with five pressure sensing holes, comprising: the blade comprises a blade pressure surface (1), a blade suction surface (2), a pressure surface rear pressure sensing hole (3), a pressure surface front pressure sensing hole (4), a leading edge point pressure sensing hole (5), a suction surface front pressure sensing hole (6), a suction surface rear pressure sensing hole (7), a pressure guide channel (8), a low-loss bent pipe (9), a blade top tenon (10), a blade root tenon (11) and a pressure guide pipe interface (12); the blade front edge is provided with a plurality of rows of pressure sensing holes along the blade height direction, each row comprises 5 pressure sensing holes positioned on the surface of the blade, namely a front edge point pressure sensing hole (5) positioned at the front edge point of the blade, a suction surface front pressure sensing hole (6) positioned at the suction surface of the suction surface (2), a suction surface rear pressure sensing hole (7) positioned at the pressure surface of the blade(1) The pressure surface rear pressure sensing holes (3) and the pressure surface front pressure sensing holes (4), the central lines of the five holes are positioned on the same blade element level, and the diameters of the pressure sensing holes are all 0.2mm to 1 mm; the central line of the pressure sensing hole (5) at the front edge point is superposed with the tangent line of the camber line of the primitive level where the central line is positioned at the front edge point; the central lines of the pressure surface rear pressure sensing hole (3) and the suction surface rear pressure sensing hole (7) are collinear, and are normals of 0.5 to 20 percent of the length point of the element level middle arc line from the element level front edge point; the central line of the front pressure sensing hole (4) of the pressure surface forms an included angle of 30-45 degrees with the central line of the rear pressure sensing hole (3) of the pressure surface and the central line of the rear pressure sensing hole (7) of the suction surface, and the central line of the front pressure sensing hole (6) of the suction surface forms an included angle of 30-45 degrees with the central lines of the rear pressure sensing hole (3) of the pressure surface and the rear pressure sensing hole (7) of the suction surface; one end of the pressure guide channel (8) is connected with the orifice of the pressure sensing hole, and the other end is connected with a pressure guide pipe interface (12) positioned in the blade top tenon (10); the diameter of the pressure guide channel (8) is consistent with that of the pressure sensing hole and ranges from 0.2mm to 1 mm; on the primitive level where the center line of the pressure sensing hole is located, the center line of a pressure guide channel (8) connected with the pressure sensing hole (5) at the leading edge point is superposed with the camber line of the primitive level of the blade, the center lines of the other pressure guide channels (8) are all equal distance lines of the center line of the pressure guide channel (8) connected with the pressure sensing hole (5) at the leading edge point, all the pressure guide channels (8) extend towards the rear of the blade at the primitive level where the pressure guide channels are located, and are bent towards the direction of a blade top tenon (10) at the chord length of 30-70% of the length from the leading edge point of the blade, and a low-loss bent pipe (9) is adopted at; the central line of the low-loss bent pipe (9) is a polar coordinate curve rho2＝a2sin2 theta, wherein a is 1 to 4 times the diameter of the pressure leading channel (8), and the curve section of the curve theta with the value between 0 and 30 degrees is the central line of the low-loss elbow (9) and is tangent with the central lines of the two connected pressure leading channels (8); the bent pressure guide channel (8) adopts a straight channel design; the center line of the pressure guide pipe interface (12) and the center line of the tail end of the pressure guide channel (8) form an included angle of 30-45 degrees, the length is 2-20 mm, and the diameter is 0.4-2 mm; after the pressure guiding pipe is connected to the pressure guiding pipe interface (12), the pressure guiding pipe can be arranged through a circumferential gap between the blade top tenon (10) and the casing installation guide rail and finally led out from an opening on the casing;
further, the blade has a plurality of rows of pressure sensing holes; the row closest to the blade root is 0.2 to 1mm away from the blade root; the row closest to the leaf top is 0.2 to 1mm away from the leaf top; and in the range of 25% of the blade height close to the blade root or close to the blade top, the distance between two adjacent rows of pressure sensing holes is 5% to 15% of the blade height, and the distance between two adjacent rows of pressure sensing holes at the rest blade heights is 10% to 20% of the blade height.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020092157.2U CN212079396U (en) | 2020-01-16 | 2020-01-16 | Element-level tenon type turbine blade with front edge provided with five pressure sensing holes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020092157.2U CN212079396U (en) | 2020-01-16 | 2020-01-16 | Element-level tenon type turbine blade with front edge provided with five pressure sensing holes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212079396U true CN212079396U (en) | 2020-12-04 |
Family
ID=73569546
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020092157.2U Withdrawn - After Issue CN212079396U (en) | 2020-01-16 | 2020-01-16 | Element-level tenon type turbine blade with front edge provided with five pressure sensing holes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212079396U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111140285A (en) * | 2020-01-16 | 2020-05-12 | 北京航空航天大学 | Element-level tenon type turbine blade with front edge provided with five pressure sensing holes |
| CN112983557A (en) * | 2021-03-01 | 2021-06-18 | 杭州汽轮动力集团有限公司 | High-temperature test piece for gas turbine blade and manufacturing method thereof |
-
2020
- 2020-01-16 CN CN202020092157.2U patent/CN212079396U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111140285A (en) * | 2020-01-16 | 2020-05-12 | 北京航空航天大学 | Element-level tenon type turbine blade with front edge provided with five pressure sensing holes |
| CN111140285B (en) * | 2020-01-16 | 2024-09-20 | 北京航空航天大学 | Tenon type turbine blade with five pressure sensing holes at primitive stage front edge |
| CN112983557A (en) * | 2021-03-01 | 2021-06-18 | 杭州汽轮动力集团有限公司 | High-temperature test piece for gas turbine blade and manufacturing method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111140542A (en) | Element-level tenon type blade with front edge provided with three pressure sensing holes | |
| CN212079396U (en) | Element-level tenon type turbine blade with front edge provided with five pressure sensing holes | |
| CN111076940A (en) | Prismatic table five-hole probe for measuring dynamic full parameters of subsonic three-dimensional flow field | |
| PL184491B1 (en) | Hull-mounted impact pressure tube | |
| KR910010034B1 (en) | Rotor blade form for the first stage of a combustion turbiine | |
| Schönweitz et al. | Experimental and numerical examinations of a transonic compressor-stage with casing treatment | |
| CN111089702A (en) | Probe for measuring full parameters of subsonic three-dimensional steady-state flow field | |
| Meyer et al. | A parameter study on the influence of fillets on the compressor cascade performance | |
| CN212079395U (en) | Handle type turbine blade with element-level front edge provided with five pressure sensing holes | |
| CN111120403A (en) | Element-level front edge handle type blade with three pressure sensing holes | |
| CN111140284B (en) | Handle type turbine blade with primitive-level front edge provided with five pressure sensing holes | |
| Pohl et al. | Variable stator vane penny gap aerodynamic measurements and numerical analysis in an annular cascade wind tunnel | |
| CN111140285B (en) | Tenon type turbine blade with five pressure sensing holes at primitive stage front edge | |
| CN212454963U (en) | Element-level tenon type blade with front edge provided with three pressure sensing holes | |
| CN106768826B (en) | Dynamic temperature and pressure combined probe for measuring ultrasonic two-dimensional unsteady flow field | |
| CN212082825U (en) | Full-parameter probe for measuring high subsonic three-dimensional steady flow field | |
| CN113586166A (en) | Turbine blade with kerosene cooling micro-channel | |
| CN107036818B (en) | Three-hole pressure leaf probe | |
| CN111498141B (en) | Method and device for realizing real-time monitoring of airflow angle based on micro probe | |
| CN111089700A (en) | Multi-point dynamic full-parameter measuring device for subsonic two-dimensional flow field | |
| CN109372788B (en) | Combined blade type probe measuring method capable of adjusting airflow parameters of stationary blade inlet | |
| CN212079741U (en) | Element-level front edge handle type blade with three pressure sensing holes | |
| MacIsaac et al. | Measurements of losses and reynolds stresses in the secondary flow downstream of a low-speed linear turbine cascade | |
| CN111089669A (en) | Device and method for accurately measuring turbine stage efficiency | |
| CN211668740U (en) | Multi-point dynamic full-parameter measuring device for subsonic two-dimensional flow field |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20201204 Effective date of abandoning: 20240920 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20201204 Effective date of abandoning: 20240920 |