CN113123834B - Blade subassembly and engine of engine - Google Patents

Blade subassembly and engine of engine Download PDF

Info

Publication number
CN113123834B
CN113123834B CN202110669085.2A CN202110669085A CN113123834B CN 113123834 B CN113123834 B CN 113123834B CN 202110669085 A CN202110669085 A CN 202110669085A CN 113123834 B CN113123834 B CN 113123834B
Authority
CN
China
Prior art keywords
outlet guide
engine
blade
guide vane
dividing wall
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.)
Active
Application number
CN202110669085.2A
Other languages
Chinese (zh)
Other versions
CN113123834A (en
Inventor
杨小贺
郑尚楠
申航
陈云永
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Commercial Aircraft Engine Co Ltd
Original Assignee
AECC Commercial Aircraft Engine Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by AECC Commercial Aircraft Engine Co Ltd filed Critical AECC Commercial Aircraft Engine Co Ltd
Priority to CN202110669085.2A priority Critical patent/CN113123834B/en
Publication of CN113123834A publication Critical patent/CN113123834A/en
Application granted granted Critical
Publication of CN113123834B publication Critical patent/CN113123834B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses a blade assembly of an engine and the engine, wherein the blade assembly comprises an outlet guide vane and a dividing wall, the outlet guide vane and the dividing wall are distributed in the circumferential direction of a duct of the engine, and the outlet guide vane and the dividing wall extend along the axial direction of the engine; the front edge of the dividing wall is positioned between two adjacent outlet guide vanes, and the front edge of the dividing wall is flush with the front edges of the outlet guide vanes; and the absolute value of the difference between the mounting angle of the dividing wall and the mounting angle of the corresponding outlet guide vane is smaller than a preset value. By adopting the invention, the number of the outer culvert guide vane blades is reduced, the weight of the engine is lightened, the total pressure recovery coefficient of the outer culvert blade assembly is improved, the inlet static pressure unevenness caused by the wall thickness blockage is reduced, the structure is more compact, the flow loss is less, the outer culvert efficiency of the engine is higher, and the outer culvert static interference noise is lower; and the flow guiding diffusion to the air flow is improved, and partial blades are prevented from working in a state of deviating from a negative attack angle and partial blades are prevented from working in a state of deviating from a positive attack angle at a design point.

Description

Blade subassembly and engine of engine
Technical Field
The invention relates to a blade assembly of an engine and the engine.
Background
The turbofan engine with a large bypass ratio is a mainstream power device of the current civil passenger plane, and the index requirements of the fuel consumption rate and the noise of the civil aviation engine are improved year by year along with the pursuit of airworthiness requirements on the economy and the environmental protection of the engine. For a turbofan engine with a large bypass ratio, the bypass efficiency has a determining factor on the oil consumption rate; the rotational-static interference noise of the fan and bypass outlet guide vanes 100 is an important component of engine noise. In a conventional high bypass ratio turbofan engine, as shown in fig. 1, the outer bypass generally has an outlet guide vane 100 and a strut 300, and the outlet guide vane 100 and the strut 300 are connected in a split manner. As shown in fig. 2, in the prior art, the outlet guide vane 100 and the support plate 300 are integrated to reduce the static interference noise of the fan of the engine, improve the bypass efficiency, and reduce the oil consumption.
In engineering application, the external culvert is usually provided with 1-2 dividing walls, and the structural form of the external culvert is related to a nacelle hanging structure scheme; an aircraft precooler needs to be installed inside the upper dividing wall, and the precooler is generally wide in size; if the lower partition wall is available, pipelines such as an anti-icing pipe and a fuel oil pipe need to be communicated with the interior of the lower partition wall. Because the thickness of the wall-dividing blade profile is very thick, the blade profile is blocked greatly, and the influence of the profile on the flow of the culvert fusion scheme is large.
In addition, because the design of the division wall, the support plate 300 and the outlet guide vane 100 fusion blade profile needs to consider two functions of internal structure installation constraint and airflow diversion diffusion, the design profile is complex, the fusion design blade profile and the adjacent outlet guide vane 100 are difficult to geometrically match, and the design difficulty is high. If the blade profile of the fusion guide blade is not matched with the design of the adjacent outlet guide blade 100, part of the blades work in a state of deviating from a negative attack angle and part of the blades work in a state of deviating from a positive attack angle under the working condition of a design point, part of the blades are separated first when deviating from the design point, and the blade group of the fusion guide blade works in a high loss area.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art that the dividing walls in the duct of the engine are fused, and provides a blade assembly of the engine and the engine.
The invention solves the technical problems through the following technical scheme:
a blade assembly of an engine, characterized in that the blade assembly comprises an outlet guide vane and a dividing wall, the outlet guide vane and the dividing wall are distributed in a circumferential direction of a duct of the engine, and both the outlet guide vane and the dividing wall extend along an axial direction of the engine;
the leading edges of the dividing walls are positioned between two adjacent outlet guide vanes, and the leading edges of the dividing walls are flush with the leading edges of the outlet guide vanes; the absolute value of the difference between the mounting angle of the dividing wall and the mounting angle of the corresponding outlet guide vane is smaller than a preset value;
wherein the mounting angle of the outlet guide vane refers to an included angle between a connecting line between a leading edge endpoint and a trailing edge endpoint of the outlet guide vane and the axis of the engine; the installation angle of the dividing wall is an included angle between a connecting line of an intersection point of the dividing wall and a front edge endpoint of the dividing wall and the axis of the engine, and the intersection point is an intersection point of a blade profile line of the dividing wall and a rear edge endpoint of the outlet guide vane.
In the scheme, the front edge of the dividing wall is positioned between two adjacent outlet guide vanes, so that the front edge of the dividing wall can be used as the outlet guide vanes, the number of the outer culvert guide vane blades is reduced, the weight of an engine is reduced, the total pressure recovery coefficient of the outer culvert blade assembly is improved, the inlet static pressure unevenness caused by the thickness blockage of the dividing wall is reduced, the structure is more compact, the flow loss is less, the outer culvert efficiency of the engine is higher, and the outer culvert static interference noise is lower; and the front edge of the dividing wall is flush with the front edge of the outlet guide vane, and the difference value between the installation angle of the dividing wall and the installation angle of the outlet guide vane meets corresponding requirements, so that the dividing wall and the outlet guide vane are fused and uniformly transited to the outlet guide vane, the diversion and diffusion of the airflow are promoted, partial blades are prevented from working in a negative attack angle state and partial blades are prevented from working in a positive attack angle state under the working condition of a design point, partial blades are prevented from being separated first when deviating from the design point, and the fused blade group works in a high loss area.
Preferably, the leaf profile line of the dividing wall comprises a leaf basin and a leaf back, and the mounting angle of the dividing wall comprises a leaf basin mounting angle and a leaf back mounting angle;
the absolute value of the difference between the mounting angle of the blade basin and the mounting angle of the outlet guide vane close to the blade basin is smaller than a first preset value, and the absolute value of the difference between the mounting angle of the blade back and the mounting angle of the outlet guide vane close to the blade back is smaller than a second preset value.
In the scheme, the installation angle relation between the leaf basin and the leaf back of the division wall and the corresponding outlet guide vanes is set according to the leaf profile line of the division wall, so that the outlet guide vanes on two sides of the division wall can be uniformly transited to the leaf basin and the leaf back of the division wall, and the leaf profiles on two sides of the division wall can be fused with the outlet guide vanes.
Preferably, the blade basin installation angle is not greater than the installation angle of the outlet guide blade close to the blade basin, and the blade back installation angle is not less than the installation angle of the outlet guide blade close to the blade back.
Preferably, the range of the absolute value of the first preset value and the range of the absolute value of the second preset value are both 1.5 degrees to 3.5 degrees.
In the scheme, the corresponding preset value can be selected according to the actual situation through the range of the first preset value and the second preset value, so that the outlet guide vane and the dividing wall are uniformly fused. In specific implementation, the first preset value and the first preset value may be the same value or different values according to actual situations.
Preferably, the absolute value of said first preset value is 2.5 °; and/or the absolute value of the second preset value is 2.5 degrees.
Preferably, the blade assembly comprises a plurality of types of outlet guide vanes, the same kind of outlet guide vanes have the same installation angle, the different kinds of outlet guide vanes have different installation angles, and the installation angles of the different kinds of outlet guide vanes gradually increase or decrease along the circumferential direction of the duct.
In this scheme, along the circumference direction of duct, have different kinds of export stator, and the erection angle between the different kinds of export stator changes gradually for the circumference transition of export stator is even, thereby can further improve the total pressure recovery coefficient of outer culvert guide vane group.
Preferably, the installation angles of the different kinds of outlet guide vanes on the blade basin side of the dividing wall are gradually increased, and the installation angles of the different kinds of outlet guide vanes on the blade back side of the dividing wall are gradually decreased.
Preferably, the number of the types of the outlet guide vanes is not less than the ratio of the difference between the blade back installation angle and the blade basin installation angle to a preset value.
Preferably, the absolute value of the difference between the stagger angles of adjacent different kinds of outlet guide vanes is not greater than a third preset value.
In this scheme, satisfy corresponding requirement between the erection angle of adjacent different kind's export stator, realized the even transition between the export stator of circumference to also can make holistic export stator can evenly transition to divider wall department, make the whole integration of blade subassembly even, reduce the flow loss, promote the efficiency of culvert outside, reduce the culvert outside and change quiet interference noise.
Preferably, the vane assembly further comprises a support plate, a leading edge of the support plate is arranged between two adjacent outlet guide vanes, and the leading edge of the support plate is flush with the leading edge of the outlet guide vane.
In this scheme, the blade subassembly still includes the extension board, and the extension board can fuse with the export stator for extension board, export stator and dividing wall can fuse and form the blade subassembly, further reduce the blade number of outer culvert export stator, alleviate engine weight, make overall structure compact.
An engine, characterized in that it comprises a blade assembly as described above.
In the scheme, the engine can reduce the number of the outer culvert guide vane blades and reduce the weight of the engine by adopting the blade assembly; the total pressure recovery coefficient of the external culvert blade assembly is improved, the static pressure unevenness of an inlet caused by the blocking of the thickness of the dividing wall is reduced, the structure is more compact, the flow loss is less, the external culvert efficiency of the engine is higher, and the static interference noise of the external culvert rotation is lower; the dividing wall and the outlet guide vane are fused and uniformly transited to the outlet guide vane, so that the flow guiding and the pressure expanding of airflow are improved, partial blades are prevented from working in a negative attack angle state and partial blades are prevented from working in a positive attack angle state under the working condition of a design point, partial blades are prevented from being separated first when the partial blades deviate from the design point, and the fused blade group works in a high loss area.
The positive progress effects of the invention are as follows: the front edge of the dividing wall is positioned between two adjacent outlet guide vanes, so that the front edge of the dividing wall can be used as an outlet guide vane, the number of outer culvert guide vane blades is reduced, the weight of an engine is reduced, the total pressure recovery coefficient of the outer culvert blade assembly is improved, the inlet static pressure unevenness caused by the thickness blockage of the dividing wall is reduced, the structure is more compact, the flow loss is less, the outer culvert efficiency of the engine is higher, and the outer culvert static interference noise is lower; and the front edge of the dividing wall is flush with the front edge of the outlet guide vane, and the difference value between the installation angle of the dividing wall and the installation angle of the outlet guide vane meets corresponding requirements, so that the dividing wall and the outlet guide vane are fused and uniformly transited to the outlet guide vane, the diversion and diffusion of the airflow are promoted, partial blades are prevented from working in a negative attack angle state and partial blades are prevented from working in a positive attack angle state under the working condition of a design point, partial blades are prevented from being separated first when deviating from the design point, and the fused blade group works in a high loss area.
Drawings
FIG. 1 is a schematic structural view of a split type bypass outlet guide vane and a support plate in the prior art;
FIG. 2 is a schematic structural view of a fused culvert outlet guide vane and a support plate in the prior art;
FIG. 3 is a schematic view of a sectional wall element stage blade profile and an adjacent outlet guide vane element stage blade profile provided by an embodiment of the invention;
FIG. 4 is a schematic cross-sectional view at 0% span S1 of an embodiment of the present invention after the division wall, the strip, and the outlet guide vane merge;
FIG. 5 is a schematic view of a blend of the dividing wall and the outlet guide vanes in the setting angle relationship provided by the embodiment of the present invention.
Description of the reference numerals
Outlet guide vanes 100
Dividing wall 200
Upper division wall 210
Pre-cooler 211
Lower dividing wall 220
Plate 300
First guide vane PS1
Third vane PS2
Fourth vane PS3
Second guide vane SS1
Fifth guide vane SS2
Engine axis L1
Leading edge endpoint line L2
Trailing edge end line L3
Leaf basin STT1
Leaf back STT 2.
Detailed Description
The invention is further illustrated by the following examples, which are not intended to limit the scope of the invention.
The embodiment of the invention provides a blade assembly of an engine, which is mainly applied to an outer duct of the engine. As shown in fig. 4, the vane assembly may include an outlet guide vane 100 and a partition wall 200 fused with each other, wherein the vane assembly typically includes 1-2 partition walls 200, and the partition wall 200 has a relatively thick thickness, and other components of the engine are typically required to be installed inside the vane assembly, for example, as shown in fig. 4, the engine has two partition walls 200, i.e., an upper partition wall 210 and a lower partition wall 220, respectively, an aircraft precooler 211 is required to be installed inside the upper partition wall 210, and a short circuit of an ice protection pipe, a fuel pipe, and the like is required to be communicated with the lower partition wall 220.
The outlet guide vanes 100 and the partition walls 200 are distributed in the circumferential direction of the duct of the engine, and both the outlet guide vanes 100 and the partition walls 200 extend in the axial direction of the engine. The leading edge of the dividing wall 200 is located between two adjacent outlet guide vanes 100, and the leading edge of the dividing wall 200 is flush with the leading edge of the outlet guide vane 100; the absolute value of the difference between the mounting angles of the division walls 200 and the corresponding mounting angles of the outlet guide vanes 100 is less than a preset value; as shown in fig. 5, the installation angle of the outlet guide vane 100 refers to an included angle between a connecting line between a leading edge endpoint and a trailing edge endpoint of the outlet guide vane 100 and the engine axis L1; the installation angle of the partition wall 200 is an included angle between a connecting line of an intersection point of the partition wall 200 and a leading edge endpoint of the partition wall 200 and the engine axis L1, and the intersection point is an intersection point at which a blade profile line of the partition wall 200 is connected with a trailing edge endpoint of the outlet guide vane 100.
In particular, as shown in fig. 3, the leading edge of the dividing wall 200 is located between two adjacent outlet guide vanes 100, and the profile at the leading edge of the dividing wall 200 is similar to the profile of the outlet guide vanes 100 and extends rearward to gradually transition to the maximum thickness of the dividing wall 200. Thereby being capable of adapting to the incoming airflow direction and geometric circumferential transition. And, at the same extension, for example as shown in fig. 4, which is a schematic cross-sectional view at 0% extension S1, the absolute value of the installation angle difference between the partition wall 200 and the corresponding outlet guide vane 100 is smaller than the preset value; correspondingly, at different elevation positions, the absolute value of the difference between the installation angles of the partition walls 200 and the corresponding outlet guide vanes 100 can also be smaller than a preset value, so that the partition walls 200 and the outlet guide vanes 100 at each elevation position can be uniformly transited to realize fusion.
Further, after the outlet guide vanes 100 are fused with the dividing walls 200, the front edges of the dividing walls 200 can serve as the outlet guide vanes 100, the number of outer culvert guide vane blades is reduced, the weight of the engine is reduced, the structure is more compact, the flow loss is smaller, the outer culvert efficiency of the engine is higher, and the outer culvert static interference noise is lower; and the uniform transition between the outlet guide vanes 100 and the dividing walls 200 can promote the flow guiding and pressure spreading of the airflow, avoid that part of the blades work in a negative attack angle state and part of the blades work in a positive attack angle state under the working condition of a design point, and avoid that part of the blades are separated first and the fused blade group works in a higher loss area when the blades deviate from the design point.
As a preferred embodiment, as shown in fig. 4, it is also possible to merge a strip 300 with the outlet guide vane 100; specifically, the leading edge of the strip 300 is disposed between two adjacent outlet guide vanes 100, and the leading edge of the strip 300 is flush with the leading edge of the outlet guide vane 100. Therefore, the number of the blades of the bypass outlet guide vane 100 is further reduced, the weight of the engine is reduced, the overall structure is compact, and the performance of the engine is improved.
The relationship of the fused characteristic parameters between the dividing wall 200 and the outlet guide vane 100 is described in detail below.
In a preferred embodiment, the leaf profile line of the division wall 200 comprises a leaf basin STT1 and a leaf back STT2, and the installation angle of the division wall 200 comprises a leaf basin installation angle and a leaf back installation angle; the absolute value of the difference between the bucket mounting angle and the mounting angle of the outlet guide vane 100 close to the bucket STT1 is smaller than a first preset value, and the absolute value of the difference between the bucket back mounting angle and the mounting angle of the outlet guide vane 100 close to the bucket back STT2 is smaller than a second preset value. Thereby enabling the outlet guide vanes 100 on both sides of the dividing wall 200 to transition to the blade basin and the blade back of the dividing wall 200 according to uniformity.
In particular implementation, as shown in fig. 5, the outlet guide vane 100 proximate to the basin STT1 is a first guide vane PS1, and the outlet guide vane 100 proximate to the blade back STT2 is a second guide vane SS 1; accordingly, the first guide vane mounting angle is alphaPS1The mounting angle of the leaf basin is alphaSTT1The second guide vane mounting angle is alphaSS1The mounting angle of the blade back is alphaSTT2。αPS1And alphaSTT1The absolute value of the difference between them is less than a first predetermined value, alphaSS1And alphaSTT2The absolute value of the difference between them is less than the second preset value.
Therein, as shown in FIG. 5, the mounting angle α of the first vane PS1PS1Is the included angle between the connecting line of the leading edge endpoint and the trailing edge endpoint of the first guide vane PS1 and the engine axis L1; leaf basin mounting angle alphaSTT1The intersection point of the vane pot STT1 is the intersection point of the line L3 connecting the trailing edge end points of the first guide vane PS1 and the second guide vane SS1 and the vane pot STT1, and is the included angle between the line connecting the intersection point of the vane pot STT1 and the leading edge end point of the partition wall 200 and the engine axis L1. Setting angle alpha of second guide vane SS1SS1The included angle between the connecting line of the leading edge end point and the trailing edge end point of the second guide vane SS1 and the engine axis L1 and the blade back installation angle alphaSTT2The intersection point of the blade back STT2 is the intersection point of the line L3 connecting the trailing edge end points of the first guide vane PS1 and the second guide vane SS1 and the blade back STT2, and is the included angle between the line connecting the intersection point of the blade back STT2 and the leading edge end point of the partition wall 200 and the engine axis L1.
As a preferred embodiment, the bucket setting angle is not greater than the setting angle of the outlet guide vane 100 near the bucket, and the blade back setting angle is not less than the setting angle of the outlet guide vane 100 near the blade back. That is, the lobe basin setting angle αSTT1No greater than the setting angle alpha of the first vane PS1PS1Blade back mounting angle alphaSTT2Not less than the setting angle alpha of the second guide vane SS1SS1。
In a preferred embodiment, the absolute value of the first preset value and the absolute value of the second preset value are both in a range of 1.5 ° to 3.5 °. Preferably, the first preset value has an absolute value of 2.5 °; and/or the absolute value of the second preset value may also range from 2.5 °.
In specific implementation, the first preset value and the first preset value may be the same value or different values according to actual situations.
As a preferred embodiment, the vane assembly comprises a plurality of types of outlet guide vanes 100, as shown in fig. 5, the leading edge end line L2 of the plurality of outlet guide vanes 100, and the leading edge of the dividing wall 200 is also on the leading edge end line L2, i.e. the leading edges of the plurality of types of outlet guide vanes 100 and the dividing wall 200 are flush. The stagger angles of the same kind of outlet guide vanes 100 are the same, the stagger angles of different kinds of outlet guide vanes 100 are different, and the stagger angles of the different kinds of outlet guide vanes 100 gradually increase or decrease along the circumferential direction of the duct. Along the circumferential direction of the culvert, different kinds of outlet guide vanes 100 are arranged, and the installation angles among the different kinds of outlet guide vanes 100 are gradually changed, so that the circumferential transition of the outlet guide vanes 100 is uniform, and the total pressure recovery coefficient of the culvert guide vane group can be further improved.
As shown in fig. 4, there are a plurality of outlet guide vanes 100 along the circumferential direction of the duct, which plurality of outlet guide vanes 100 may in turn be divided into different types. As shown in fig. 5, take 8 outlet guide vanes 100 near both sides of the dividing wall 200 as an example, wherein the outlet guide vanes 100 near the vane basin are of three types, a first guide vane PS1, a third guide vane PS2 and a fourth guide vane PS 3; the outlet guide vanes 100 near the blade back are of two types, second guide vane SS1 and fifth guide vane SS 2.
As a preferred embodiment, the stagger angles of the different kinds of outlet guide vanes 100 on the basin side of the division wall 200 gradually increase, and the stagger angles of the different kinds of outlet guide vanes 100 on the back side of the division wall 200 gradually decrease.
As shown in fig. 5, the mounting angle has a gradually increasing trend from the vane pot STT1 to the first, third and fourth vanes PS1, PS2, PS 3; from the blade back STT2 to the second guide vane SS1 and the fifth guide vane SS2, the installation angle of the guide vanes gradually decreases, so that the installation angle between the division wall 200 and the outlet guide vane 100 can be uniformly transited and fused in the circumferential direction of the outer duct, and the flow guiding effect of the air flow is improved.
As a preferred embodiment, the number of types of the outlet guide vanes 100 is not less than the ratio of the difference between the blade back mounting angle and the blade basin mounting angle to a preset value.
That is, the number N of blade types of the circumferential outlet guide vane 100 may satisfy the following relationship:
Figure DEST_PATH_IMAGE001
。
as the outlet guide vane 100 in FIG. 4 needs to adapt to the blade profile geometry of the division wall 200, the geometric transition is usually realized by adopting 9-15 blade profiles in the circumferential direction.
As a preferred embodiment, the absolute value of the difference between the stagger angles of the adjacent different kinds of outlet guide vanes 100 is not more than the third preset value.
The absolute value of the third preset value ranges from 1.5 degrees to 3.5 degrees. Preferably, the third preset value may be 2.5 °. That is, the difference between the third vane PS2 and the first vane PS1, and the difference between the fourth vane PS3 and the third vane PS2 do not exceed 2.5 °; the difference between the second vane SS1 and the fifth vane SS2 also does not exceed 2.5.
Embodiments of the present invention also provide an engine, which includes a blade assembly of the engine as described above. The vane assembly may be disposed at a circumferential location of an outer duct of the engine.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.

Claims (11)

1. A blade assembly of an engine, characterized in that the blade assembly comprises an outlet guide vane and a dividing wall, the outlet guide vane and the dividing wall are distributed in a circumferential direction of a duct of the engine, and both the outlet guide vane and the dividing wall extend along an axial direction of the engine;
the leading edges of the dividing walls are positioned between two adjacent outlet guide vanes, and the leading edges of the dividing walls are flush with the leading edges of the outlet guide vanes; the absolute value of the difference between the mounting angle of the dividing wall and the mounting angle of the corresponding outlet guide vane is smaller than a preset value;
wherein the mounting angle of the outlet guide vane refers to an included angle between a connecting line between a leading edge endpoint and a trailing edge endpoint of the outlet guide vane and the axis of the engine; the installation angle of the dividing wall is an included angle between a connecting line of an intersection point of the dividing wall and a front edge endpoint of the dividing wall and the axis of the engine, and the intersection point is an intersection point of a blade profile line of the dividing wall and a rear edge endpoint of the outlet guide vane.
2. The blade assembly of the engine according to claim 1, characterized in that the profiled blade line of the dividing wall comprises a blade basin and a blade back, and the mounting angle of the dividing wall comprises a blade basin mounting angle and a blade back mounting angle;
the absolute value of the difference between the mounting angle of the blade basin and the mounting angle of the outlet guide vane close to the blade basin is smaller than a first preset value, and the absolute value of the difference between the mounting angle of the blade back and the mounting angle of the outlet guide vane close to the blade back is smaller than a second preset value.
3. The blade assembly of the engine of claim 2, characterized in that the bucket fillet is not greater than the fillet of an outlet guide vane proximate to the bucket, and the bucket back fillet is not less than the fillet of an outlet guide vane proximate to the bucket back.
4. The blade assembly of an engine according to claim 2, characterized in that the range of absolute values of said first preset value and of said second preset value is from 1.5 ° to 3.5 °.
5. The blade assembly of an engine according to claim 4, characterized in that the absolute value of said first preset value is 2.5 °; and/or the absolute value of the second preset value is 2.5 degrees.
6. The blade assembly of the engine according to claim 1, characterized in that the blade assembly comprises a plurality of types of the outlet guide vanes, the angle of incidence of the outlet guide vanes of a same type is the same, the angle of incidence of the outlet guide vanes of different types differs, and the angle of incidence of the outlet guide vanes of different types gradually increases or decreases along the circumferential direction of the duct.
7. The blade assembly of the engine according to claim 6, characterized in that the stagger angles of the different kinds of outlet guide vanes located at the basin side of the dividing wall are gradually increased and the stagger angles of the different kinds of outlet guide vanes located at the blade back side of the dividing wall are gradually decreased.
8. The blade assembly of the engine according to claim 6, characterized in that the number of types of outlet guide vanes is not less than a ratio of a difference of a blade back mount angle and a blade basin mount angle to a preset value.
9. The blade assembly of the engine according to claim 6, characterized in that an absolute value of a difference between the stagger angles of adjacent different kinds of outlet guide vanes is not greater than a third preset value.
10. The blade assembly of the engine of claim 1, further comprising a brace plate, a leading edge of the brace plate being disposed between two adjacent outlet guide vanes, and a leading edge of the brace plate being flush with a leading edge of the outlet guide vane.
11. An engine, characterized in that it comprises a vane assembly of an engine according to any one of claims 1-10.
CN202110669085.2A 2021-06-17 2021-06-17 Blade subassembly and engine of engine Active CN113123834B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110669085.2A CN113123834B (en) 2021-06-17 2021-06-17 Blade subassembly and engine of engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110669085.2A CN113123834B (en) 2021-06-17 2021-06-17 Blade subassembly and engine of engine

Publications (2)

Publication Number Publication Date
CN113123834A CN113123834A (en) 2021-07-16
CN113123834B true CN113123834B (en) 2021-09-28

Family

ID=76783026

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110669085.2A Active CN113123834B (en) 2021-06-17 2021-06-17 Blade subassembly and engine of engine

Country Status (1)

Country Link
CN (1) CN113123834B (en)

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1291235A (en) * 1968-10-02 1972-10-04 Rolls Royce Fluid flow machine
US8221071B2 (en) * 2008-09-30 2012-07-17 General Electric Company Integrated guide vane assembly
DE102010014900A1 (en) * 2010-04-14 2011-10-20 Rolls-Royce Deutschland Ltd & Co Kg Secondary flow channel of a turbofan engine
FR3004749B1 (en) * 2013-04-22 2015-05-08 Snecma STATOR WHEEL, RECTIFIER AUB WHEEL, TURBOMACHINE EQUIPPED WITH SUCH WHEEL, AND METHOD OF DISTORTION COMPENSATION IN SUCH A WHEEL
FR3032480B1 (en) * 2015-02-09 2018-07-27 Safran Aircraft Engines AIR RECOVERY ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE
FR3032495B1 (en) * 2015-02-09 2017-01-13 Snecma RECOVERY ASSEMBLY WITH OPTIMIZED AERODYNAMIC PERFORMANCE
CN204511524U (en) * 2015-03-18 2015-07-29 中国科学院工程热物理研究所 A kind of inlet guide vane structure of turbomachine non-axisymmetric distribution
GB201703422D0 (en) * 2017-03-03 2017-04-19 Rolls Royce Plc Gas turbine engine vanes
CN207728397U (en) * 2017-12-29 2018-08-14 沂源县华阳能源设备有限公司 Control Stage of Steam Turbine nozzle sets
CN210919269U (en) * 2019-11-22 2020-07-03 中国航发商用航空发动机有限责任公司 Turbofan engine and fusion support plate inner duct thereof

Also Published As

Publication number Publication date
CN113123834A (en) 2021-07-16

Similar Documents

Publication Publication Date Title
US8616843B2 (en) Turbo machinery
RU2715131C2 (en) Gas turbine engine air flow straightening unit with improved aerodynamic characteristics
JP6740271B2 (en) Impeller and centrifugal compressor equipped with this impeller
CN106246408B (en) A kind of ultra-compact high blending efficiency racemization lobe mixing exhaust system architecture
CA2935758A1 (en) Integrated strut-vane nozzle (isv) with uneven vane axial chords
EP3147464B1 (en) Expansion turbine and turbocharger
CN103016069B (en) Air cycle machine, for its turbine nozzle and turbine nozzle installation method
CN105864105A (en) Axial flow compressor stator with in-vitro small blades in hub corner area
CN104632701A (en) High-bypass-ratio turbo-fan engine fan long-short blade structure
US2974858A (en) High pressure ratio axial flow supersonic compressor
US8152459B2 (en) Airfoil for axial-flow compressor capable of lowering loss in low Reynolds number region
CN108953223B (en) Centrifugal impeller
JP2002213202A (en) Gas turbine blade
CN115962155A (en) Adjustable shunting type slotted blade diffuser and centrifugal compressor thereof
CN203614229U (en) Fusion outer bypass outlet guide vane support plate structure of engine and aero-engine
CN113123834B (en) Blade subassembly and engine of engine
WO2023050692A1 (en) Stator vane distortion-resistant axial-flow compressor and stator vane distortion-resistant method for axial-flow compressor
CN110775283B (en) Blade assembly for distribution of stratified fluids in an aircraft
EP3508685B1 (en) Turbine wheel, turbine, and turbocharger
CN109630468A (en) Diffuser positioning device
CN108443218B (en) Pump impeller with secondary splitter blade
CN114607641B (en) Guide vane structure of axial flow fan and axial flow fan
US4934139A (en) Turbofan gas turbine engine
CN113864243A (en) Axial flow compressor for improving full-circumferential flow field
CN208534836U (en) A kind of multi-wing centrifugal fan blade

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant