CN114329771B - Axial flow compressor size calculation method considering blade installation angle - Google Patents

Axial flow compressor size calculation method considering blade installation angle Download PDF

Info

Publication number
CN114329771B
CN114329771B CN202111528129.6A CN202111528129A CN114329771B CN 114329771 B CN114329771 B CN 114329771B CN 202111528129 A CN202111528129 A CN 202111528129A CN 114329771 B CN114329771 B CN 114329771B
Authority
CN
China
Prior art keywords
rotor blade
inlet
stage
stage rotor
axial
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
CN202111528129.6A
Other languages
Chinese (zh)
Other versions
CN114329771A (en
Inventor
陈玉春
陈敏泽
李孙洋
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.)
Northwestern Polytechnical University
Original Assignee
Northwestern Polytechnical University
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 Northwestern Polytechnical University filed Critical Northwestern Polytechnical University
Priority to CN202111528129.6A priority Critical patent/CN114329771B/en
Publication of CN114329771A publication Critical patent/CN114329771A/en
Application granted granted Critical
Publication of CN114329771B publication Critical patent/CN114329771B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Landscapes

  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a method for calculating the size of an equal-inner-diameter axial flow compressor by considering the installation angle of a blade, which comprises the steps of calculating the tangential velocity of the blade tip of an inlet-stage rotor blade to be U according to the section parameters of the inlet-stage of the equal-inner-diameter axial flow compressor Tin And the axial velocity U of the air flow of the inlet stage rotor blades zin Forming a speed triangle, and calculating the installation angle a of the inlet-stage rotor blade according to the trigonometric function relation of the speed triangle in Thereby obtaining the axial length L of the inlet-stage rotor blade gin The method comprises the steps of carrying out a first treatment on the surface of the Meanwhile, according to the characteristics of the equal-inner-diameter axial flow compressor, the axial length L of the outlet-stage rotor blade is obtained gout Thus obtaining the estimated total length size of the equal-inner-diameter axial flow compressor. The method can rapidly and accurately estimate the size of the axial flow compressor by taking the factors of the blade mounting angle into consideration when designing the overall scheme of the aero-engine.

Description

Axial flow compressor size calculation method considering blade installation angle
Technical Field
The invention belongs to the field of aviation turbine engines, and particularly relates to a method for calculating the size of an axial flow compressor by considering the installation angle of a blade.
Background
The axial flow compressor is a key component of the aero-turbine engine, and the size estimation of the axial flow compressor is an important link in the overall design technology of the aero-turbine engine. The existing size pre-estimation calculation method of the axial flow compressor still has the problems of insufficient precision, large calculation error and the like in the calculation process although a plurality of influencing factors such as hub ratio, aspect ratio and the like are considered, and the inaccuracy of the size brings a plurality of inconveniences to component designers in the detailed design.
Disclosure of Invention
The invention aims to avoid the defects of the prior art and provide the axial flow compressor size calculation method taking the blade installation angle into consideration, which improves the calculation accuracy of the axial flow compressor, shortens the design iteration period and improves the design efficiency.
In order to achieve the above purpose, the technical scheme adopted by the invention is a method for calculating the size of the equal-inner-diameter axial flow compressor by considering the installation angle of a blade, which comprises the following steps:
step one, calculating to obtain the outer diameter D of an inlet-stage rotor blade of the equal-inner-diameter axial-flow compressor according to the inlet-stage section parameters of the equal-inner-diameter axial-flow compressor Tin And chord length C of inlet stage rotor blade Bin The method comprises the steps of carrying out a first treatment on the surface of the Then according to the first-stage pressure ratio Pr of the axial-flow compressor 1 Fitting relation with the tangential velocity of the blade tip of the inlet-stage rotor blade to obtain the tangential velocity of the blade tip of the inlet-stage rotor blade as U Tin And the axial velocity U of the air flow of the inlet stage rotor blades Zin ；
Step two, the tangential velocity of the blade tip of the inlet-stage rotor blade obtained in the step one is U Tin And the axial velocity U of the air flow of the inlet stage rotor blades Zin Forming a speed triangle, and calculating the installation angle a of the inlet-stage rotor blade according to the trigonometric function relation of the speed triangle in The installation angle a in For inlet stage rotor blade chord C in the direction of blade rotation Bin Axial length L to inlet stage rotor blade gin Is included in the plane of the first part;
step three, according to the trigonometric function relation in the step two, the chord length C of the inlet-stage rotor blade obtained in the step one Bin And step two, obtaining the installation angle a of the inlet-stage rotor blade in Obtaining the axial length La of the inlet-stage moving rotor blade in Since the axial length of the rotor blade comprises the movable blades and the static blades and the gaps between the movable blades and the static blades, the axial length factor L of the rotor blade is inserted r Obtaining the axial length L of the inlet-stage rotor blade gin The method comprises the following steps:
L gin ＝L ain ×L r ；
i.e. the axial length L of the rotor blade of the inlet stage is obtained gin ；
Step four, knowing the inlet-stage rotor blade according to the characteristics of the equal-inner-diameter axial flow compressorSheet inner diameter D Hin With the inner diameter D of the rotor blade of the outlet stage Hout Equal, the axial length L of the rotor blade of the outlet stage is calculated according to the steps one to three gout And an outlet stage rotor blade outer diameter D Tout ；
Step five, according to the formula:
L＝(L gin +L gout )×N Z /2
in N Z And obtaining the estimated total length size L of the equal-diameter axial flow compressor for the equal-diameter axial flow compressor.
Further, the first step specifically includes the following steps:
step 11, the inlet stage rotor blade and outlet stage section parameters of the axial flow compressor comprise: inlet stage rotor blade Mach number Ma in Mach number of exit stage rotor blade Ma out The method comprises the steps of carrying out a first treatment on the surface of the Inlet stage rotor blade flow W in The flow of the rotor blade of the outlet stage is W out The method comprises the steps of carrying out a first treatment on the surface of the The total temperature of the inlet-stage rotor blade is T in The total temperature of the rotor blade of the outlet stage is T out The method comprises the steps of carrying out a first treatment on the surface of the The total pressure of the inlet-stage rotor blade is P in The total pressure of the rotor blade of the outlet stage is P out The method comprises the steps of carrying out a first treatment on the surface of the The gas-oil ratio of the inlet-stage rotor blade is f in The gas-oil ratio of the rotor blade at the outlet stage is f out The method comprises the steps of carrying out a first treatment on the surface of the Calculating the area of the inlet-stage rotor blade ring to be A in The area of the ring of the rotor blade at the outlet stage is A out ；
Step 12, inlet stage rotor blade ring area A according to step 11 in And exit stage rotor blade ring area A out And the inlet stage hub ratio HTR of known axial flow compressors in Calculating the outer diameter D of the inlet-stage rotor blade Tin And the inlet stage rotor blade inner diameter D Hin The method comprises the steps of carrying out a first treatment on the surface of the Thereby obtaining the blade height H of the inlet stage rotor blade Bin Pitch diameter D of inlet stage rotor blade Min The method comprises the steps of carrying out a first treatment on the surface of the Finally, according to the inlet stage rotor blade aspect ratio AR in Obtaining chord length C of the inlet-stage rotor blade Bin ；
Step 13, according to the first stage pressure ratio of the axial flow compressorPr 1 Tangential velocity U to tip of inlet stage rotor blade Tin Obtaining the tangential velocity of the blade tip of the inlet-stage rotor blade as U Tin The method comprises the steps of carrying out a first treatment on the surface of the Then according to the section parameters of the inlet-stage rotor blade of the axial-flow compressor, the air flow axial speed U of the inlet-stage rotor blade is calculated Zin 。
Further, the step 11 specifically includes:
according to the flow continuity equation:
in the method, in the process of the invention,wherein k is an adiabatic index, R is a gas constant, and the value of a speed factor lambda is 0-1, so that the area of an inlet-stage rotor blade ring of the axial flow compressor is calculated to be A in And an exit stage rotor blade ring area A out 。
Further, the step 12 specifically includes:
step 121, according to the inlet stage ring area A of the axial flow compressor in Hub ratio HTR to inlet stage of axial compressor in From the geometric equation:
calculating the outer diameter D of the inlet stage rotor blade Tin ；
Step 122, according to the formula:
HTR in ＝D Hin /D Tin
obtaining the inner diameter D of the inlet-stage rotor blade of the axial-flow compressor Hin ；
Step 123, according to the inlet stage rotor blade outer diameter D of said axial flow compressor rotor blade Tin And an inlet stage rotor blade inner diameter D Hin The formula is introduced:
H Bin ＝(D Tin -D Hin )/2
D Min ＝(D Tin +D Hin )/2
calculating the blade height H of the inlet stage rotor blade Bin Pitch diameter D of inlet stage rotor blade Min ；
Step 124, according to the obtained inlet stage rotor blade height H Bin And inlet stage rotor blade aspect ratio AR in By the formula:
C Bin ＝H Bin /AR in
calculating chord length C of inlet-stage rotor blade of axial flow compressor Bin 。
Further, the step 13 specifically includes:
step 131, the tangential velocity of the tip of the inlet-stage rotor blade of the axial flow compressor is U Tin The calculation formula is as follows:
U Tin ＝(-398.46+682.61×Pr 1 -100.38×Pr 1 2 )×(T in /288.15) 0.5 ；
wherein Tin is the total temperature, pr of the inlet-stage rotor blade 1 A first stage pressure ratio for the axial flow compressor;
step 132, the formula:
U Zin ＝Ma in ×Cs
wherein: cs is sonic, ma in Is the Mach number of the rotor blade of the inlet stage, and the axial speed U of the air flow of the rotor blade of the inlet stage is obtained Zin 。
Further, in the second step, the installation angle a of the inlet stage rotor blade in The calculation formula of (2) is as follows:
in U Zin For the axial velocity of the air flow of the rotor blades of the inlet stage, U Tin For the purpose of importBlade tip tangential speed of the sub-blade.
Further, the inlet-stage moving rotor blade axial length La in the third step in The calculation formula of (2) is as follows:
wherein: a, a in C for the mounting angle of the inlet stage rotor blade Bin Is the chord length of the inlet stage rotor blade.
Further, the fourth step is specifically calculated according to the steps one to three in sequence: the area of the ring of the rotor blade of the outlet stage is A out Hub ratio HTR of outlet stage rotor blades out Outer diameter D of outlet stage rotor blade Tout Pitch diameter D of outlet stage rotor blade Mout Blade height H of an outlet stage rotor blade Bout Aspect ratio AR of outlet stage rotor blade out Chord length C of outlet stage rotor blade Bout Tangential speed U of outlet-stage blade tip Tout Air flow axial velocity U of outlet stage rotor blade zout The method comprises the steps of carrying out a first treatment on the surface of the Thereby, the mounting angle a of the outlet stage rotor blade is obtained out Axial length L of outlet-stage rotor blade aout The method comprises the steps of carrying out a first treatment on the surface of the Finally, according to the formula:
L gout ＝L aout ×L r ；
obtain the axial length L of the rotor blade of the outlet stage gout 。
Further, the outlet stage blade tip tangential velocity U Tout Is calculated as follows:
by the outer diameter D of the inlet stage rotor blades Tin According to the formula:
U Tin ＝(π/60)D Tin N
calculating the rotating speed N of the axial flow compressor, and then according to the formula:
U Tout ＝(π/60)D Tout N
wherein: d (D) Tout Obtaining an outlet for the outer diameter of the outlet stage rotor bladeStage tip tangential velocity U Tout 。
Further, wherein the outlet stage rotor blade to hub ratio HTR of the axial compressor out And outer diameter D of the outlet stage rotor blade Tout The specific calculation of (3) is as follows: from the characteristics of the equal-diameter axial-flow compressor, the inner diameter D of the inlet-stage rotor blade can be known Hin With the inner diameter D of the rotor blade of the outlet stage Hout The values of the two are equal to each other,
then according to the outlet stage ring area A of the axial flow compressor out And an outlet stage rotor blade inner diameter D Hout From the geometric equation:
HTR out ＝D Hout /D Tout
calculating an outlet stage rotor blade hub ratio HTR of the axial flow compressor out And outer diameter D of the outlet stage rotor blade Tout 。
The beneficial effects of the invention are as follows: the method and the device can rapidly and accurately estimate the size of the axial flow compressor by taking the influence factors of the blade mounting angles into consideration when the overall scheme design of the aero-engine is carried out, provide more visual axial flow compressor expression forms for overall designers, facilitate the overall designers to carry out optimization iteration on the overall performance of the axial flow compressor, shorten the design iteration period and guide component designers to carry out detailed scheme design of the axial flow compressor.
Drawings
FIG. 1 is a flow chart of an axial compressor sizing calculation;
FIG. 2 is a flow chart for calculating stage length considering blade mounting angle;
fig. 3 is a schematic view of a speed triangle similar to a mounting angle triangle.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.
In order to achieve the above object, the present invention provides the following embodiments:
example 1: a method for calculating the size of an equal-inner-diameter axial flow compressor by considering the installation angle of a blade comprises the following steps:
101. according to the inlet-stage section parameters of the equal-inner-diameter axial flow compressor, the inlet-stage rotor blades and the outlet-stage section parameters of the axial flow compressor comprise: inlet stage rotor blade Mach number Ma in Mach number of exit stage rotor blade Ma out The method comprises the steps of carrying out a first treatment on the surface of the Inlet stage rotor blade flow W in The flow of the rotor blade of the outlet stage is W out The method comprises the steps of carrying out a first treatment on the surface of the The total temperature of the inlet-stage rotor blade is T in The total temperature of the rotor blade of the outlet stage is T out The method comprises the steps of carrying out a first treatment on the surface of the The total pressure of the inlet-stage rotor blade is P in The total pressure of the rotor blade of the outlet stage is P out The method comprises the steps of carrying out a first treatment on the surface of the The gas-oil ratio of the inlet-stage rotor blade is f in The gas-oil ratio of the rotor blade at the outlet stage is f out ；
According to the flow continuity equation:
in the method, in the process of the invention,wherein k is an adiabatic index, R is a gas constant, and the value of a speed factor lambda is 0-1, so that the area of an inlet-stage rotor blade ring of the axial flow compressor is calculated to be A in And an exit stage rotor blade ring area A out ；
102. According to the inlet stage ring area A of the axial flow compressor in Hub ratio HTR to inlet stage of axial compressor in From the geometric equation:
calculating the outer diameter D of the inlet stage rotor blade Tin ；
103. According to the formula:
HTR in ＝D Hin /D Tin
obtaining the inner diameter D of the inlet-stage rotor blade of the axial-flow compressor Hin ；
104. According to the outer diameter D of the inlet stage rotor blade of the axial flow compressor rotor blade Tin And an inlet stage rotor blade inner diameter D Hin The formula is introduced:
H Bin ＝(D Tin -D Hin )/2
D Min ＝(D Tin +D Hin )/2
calculating the blade height H of the inlet stage rotor blade Bin Pitch diameter D of inlet stage rotor blade Min ；
105. According to the obtained blade height H of the inlet-stage rotor blade Bin And inlet stage rotor blade aspect ratio AR in By the formula:
C Bin ＝H Bin /AR in
calculating chord length C of inlet-stage rotor blade of axial flow compressor Bin 。
106. Calculating the tangential velocity of the blade tip of an inlet-stage rotor blade of an axial flow compressor as U Tin The calculation formula is as follows:
U Tin ＝(-398.46+682.61×Pr 1 -100.38×Pr 1 2 )×(T in /288.15) 0.5 ；
wherein Tin is the total temperature, pr of the inlet-stage rotor blade 1 A first stage pressure ratio for the axial flow compressor;
107. the formula is:
U Zin ＝M ain ×Cs
wherein: cs is sonic velocity, M ain Is the Mach number of the rotor blade of the inlet stage, and the axial speed U of the air flow of the rotor blade of the inlet stage is obtained Zin 。
108. The inlet stage rotor blade tip tangential velocity resulting from said step 106 is U Tin And the inlet stage rotor obtained in step 107Axial velocity U of blade air flow Zin Forming a speed triangle, and according to the trigonometric function relation of the speed triangle and the formula
In U Zin For the axial velocity of the air flow of the rotor blades of the inlet stage, U Tin For the tangential velocity of the tip of an inlet stage rotor blade, the installation angle a of the inlet stage rotor blade is calculated in The installation angle a in For inlet stage rotor blade chord C in the direction of blade rotation Bin Axial length L to inlet stage rotor blade gin Is included in the plane of the first part;
109. the chord length C of the inlet stage rotor blade from step 105 is based on the trigonometric function relationship of 108 Bin And the angle a of the velocity triangle obtained in step 108 in According to the formula
Wherein: a, a in C for the mounting angle of the inlet stage rotor blade Bin For the chord length of the inlet-stage rotor blade, the axial length La of the inlet-stage rotor blade is obtained in Since the axial length of the rotor blade comprises the movable blades and the static blades and the gaps between the movable blades and the static blades, the axial length factor L of the rotor blade is inserted r Obtaining the axial length L of the inlet-stage rotor blade gin The method comprises the following steps:
L gin ＝La in ×L r ；
i.e. the axial length L of the rotor blade of the inlet stage is obtained gin ；
110. From the characteristics of the equal-diameter axial-flow compressor, the inner diameter D of the inlet-stage rotor blade can be known Hin With the inner diameter D of the rotor blade of the outlet stage Hout The values of the two are equal to each other,
then according to the area Aout and outlet of the outlet stage ring of the axial-flow compressorStage rotor blade inner diameter D Hout From the geometric equation:
HTR out ＝D Hout /D Tout
calculating an outlet stage rotor blade hub ratio HTrout and an outer diameter D of an outlet stage rotor blade of the axial flow compressor Tout ；
111. According to the outer diameter D of the outlet stage rotor blade of the axial flow compressor rotor blade Tout And an outlet stage rotor blade inner diameter D Hout The formula is introduced:
H Bout ＝(D Tout -D Hout )/2
D Mout ＝(D Tout +D Hout )/2
calculating the blade height H of the outlet stage rotor blade Bout Pitch diameter D of outlet stage rotor blade Mout ；
112. According to the obtained blade height H of the outlet stage rotor blade Bout And an outlet stage rotor blade aspect ratio AR in By the formula:
C Bout ＝H Bout /AR out
calculating chord length C of outlet-stage rotor blade of axial flow compressor Bout ；
113. By the outer diameter D of the inlet stage rotor blades Tin Calculating the tangential velocity of the blade tip of an outlet-stage rotor blade of an axial flow compressor as U Tout The calculation formula is as follows:
U Tin ＝(π/60)D Tin N
calculating the rotating speed N of the axial flow compressor, and then according to the formula:
U Tout ＝(π/60)D Tout N
wherein: d (D) Tout Obtaining the tangential velocity U of the tip of the outlet stage for the outer diameter of the outlet stage rotor blade Tout.
114. The formula is:
U Zout ＝Ma in ×Cs
wherein: cs is sonic, ma out Is the Mach number of the rotor blade of the outlet stage, and the axial velocity U of the air flow of the rotor blade of the outlet stage is obtained Zout ；
115. The tip tangential velocity of the outlet stage rotor blade resulting from the step 113 is U Tout And the outlet stage rotor blade air flow axial velocity U of the outlet stage rotor blade obtained in step 114 Zout Forming a speed triangle, and according to the trigonometric function relation of the speed triangle and the formula
In U Zout For the axial velocity of the air flow of the rotor blade of the outlet stage, U Tout For the tangential velocity of the blade tip of the inlet-stage rotor blade, calculating the installation angle a of the outlet-stage rotor blade in The installation angle a in For the chord length C of the rotor blade of the outlet stage in the direction of rotation of the blade Bin Axial length L with the rotor blade of the outlet stage gin Is included in the plane of the first part;
116. according to the trigonometric function relationship of 115, the chord C of the outlet stage rotor blade resulting from step 112 Bout And the mounting angle a of the outlet stage rotor blade obtained in step 115 in According to the formula:
wherein: a, a out C for the mounting angle of the inlet stage rotor blade Bout For the chord length of the rotor blade of the outlet stage, the axial length L of the rotor blade of the outlet stage is obtained aout Since the axial length of the rotor blade comprises the movable blades and the static blades and the gaps between the movable blades and the static blades, the axial length factor L of the rotor blade is inserted r Obtaining the outlet-stage rotor bladeSheet axial length L gout The method comprises the following steps:
L gout ＝L aout ×L r ；
i.e. the axial length L of the rotor blade of the outlet stage is obtained gout ；
117. According to the formula:
L＝(L gin +L gout )×N/2
wherein: l (L) gout For the outlet stage rotor blade axial length, L, obtained in step 116 gin And obtaining the estimated total length dimension L of the equal-inner-diameter axial flow compressor for the axial length of the outlet-stage rotor blade obtained in the step 109.
The calculation example of the present invention uses a total pressure ratio pr=8 and a number of stages N Z For example, the method for calculating the size of the inner diameter axial flow compressor according to the present invention, which is =10, comprises:
(1) In this embodiment, taking the calculation of a specific axial flow compressor as an example, when the calculation of the size of the axial flow compressor is performed, the parameters of the inlet and outlet section of the axial flow compressor are required, including the mach number (Ma in ＝0.4，Ma out Inlet and outlet flow rate (w=0.3) in ＝60.41kg/s，W out =47.12 kg/s), total inlet and outlet temperature (T in ＝415.34K，T out Inlet and outlet total pressure (P) = 784.27K in ＝316640.6Pa，P out Inlet-outlet gas-oil ratio (f) = 2533125 Pa) in ＝0，f out ＝0)。
(2) According to the above parameters, the flow rate continuous equation:
in the formula, with respect to air,wherein k=1.4, R=287.4J/(kg.K), the value of the speed factor lambda is 0-1, and the inlet and outlet area A of the axial flow compressor can be calculated in =0.165 and a out ＝0.045。
(3) By a given inlet stage hub ratio HTR in =0.72 and calculated inlet stage area a in ＝0.165m 2 From geometric equations
The outer diameter D of the inlet stage rotor blade can be calculated Tin ＝0.637m。
(4) Known inlet stage hub ratio HTR in =0.72, inlet stage outer diameter D Tin =0.637m, according to the formula
HTR in ＝D Hin /D Tin
Calculating the inner diameter D of the inlet stage Hin ＝0.46m；
(5) According to the calculated D Hin ＝0.46m，D Tin =0.637m, expressed by the formula
H Bin ＝(D Tin -D Hin )/2
D Min ＝(D Tin +D Hin )/2
Calculating the blade height H of an inlet stage rotor blade Bin =0.089 m and pitch diameter D of inlet stage rotor blade Min ＝0.548m。
(6) H calculated from the foregoing Bin =0.089 m and known conditional inlet stage rotor blade aspect ratio AR in =3.9, according to the formula
C Bin ＝H Bin /AR in
Calculating chord C of an inlet stage rotor blade Bin ＝0.023。
(7) The total pressure ratio Pr=8 and the series N are designed by the axial flow compressor with the known condition Z =10, according to the characteristics of an equal-bore axial compressor: equal-power equal-polytropic efficiency for calculating first-stage pressure ratio Pr of axial-flow compressor 1 =1.32; according to the fitting relation of the pressure ratio and the blade tip tangential speed, adopting the formula:
U Tin ＝(-398.46+682.61×Pr 1 -100.38×Pr 1 2 )×(T in /288.15) 0.5 ；
obtaining the tangential velocity U of the blade tip of the inlet-stage rotor blade Tin ＝412.5m/s；
(8) According to the section parameters of the inlet stage of the compressor, the formula is adopted:
U Zin ＝M ain ×Cs
calculating the axial velocity U of the air flow of the rotor blade of the inlet stage Zin ＝160.6m/s；
Tip tangential speed U of the inlet stage rotor blade Tin And the axial velocity U of the air flow of the inlet stage rotor blades Zin Forming a speed triangle, calculating a blade mounting angle a=21.27 DEG according to a trigonometric function relation, wherein the speed triangle is similar to the blade mounting angle triangle, and the chord length C of the blade is known B The axial length lain=0.0083 m of the vane can be calculated according to the triangle geometry relation, the rotor stage length of the compressor comprises the moving vane, the static vane and the gap, the axial flow compressor needs to be inserted into the length factor lr=7 of the compressor according to the formula:
L gin ＝L ain ×L r
obtaining the stage length L of the compressor gin ＝0.058。
(9) The equal diameter mode of the axial flow compressor is equal diameter mode, namely the inlet and outlet rotors of the axial flow compressor have equal diameter, D Hin ＝D Hout =0.46 m. According to the calculation steps, the dimension parameters of the outlet of the axial compressor are calculated, and the outer diameter D of the outlet of the axial compressor can be calculated Tout Stage length L of outlet rotor =0.518 m gout ＝0.042m。
(10) The estimated size of the axial compressor is mainly represented by the length and the outer diameter thereof, and the total length of the axial compressor is represented by the formula l= (L) gin +L gout )×N Z 2=0.5m. Inlet stage outer diameter D of compressor Tin =0.637m and an outlet outside diameter D Tout ＝0.518m。
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.

Claims (10)

1. The method for calculating the size of the equal-inner-diameter axial flow compressor by considering the installation angle of the blade is characterized by comprising the following steps of:
step one, calculating to obtain the outer diameter D of an inlet-stage rotor blade of the equal-inner-diameter axial-flow compressor according to the inlet-stage section parameters of the equal-inner-diameter axial-flow compressor Tin And chord length C of inlet stage rotor blade Bin The method comprises the steps of carrying out a first treatment on the surface of the Then according to the first-stage pressure ratio Pr of the axial-flow compressor 1 Fitting relation with the tangential velocity of the blade tip of the inlet-stage rotor blade to obtain the tangential velocity of the blade tip of the inlet-stage rotor blade as U Tin And the axial velocity U of the air flow of the inlet stage rotor blades Zin ；
Step two, the tangential velocity of the blade tip of the inlet-stage rotor blade obtained in the step one is U Tin And the axial velocity U of the air flow of the inlet stage rotor blades Zin Forming a speed triangle, and calculating the installation angle a of the inlet-stage rotor blade according to the trigonometric function relation of the speed triangle in The installation angle a in For inlet stage rotor blade chord C in the direction of blade rotation Bin Axial length L to inlet stage rotor blade gin Is included in the plane of the first part;
step three, according to the trigonometric function relation in the step two, the chord length C of the inlet-stage rotor blade obtained in the step one Bin And the installation angle a of the inlet-stage rotor blade obtained in the second step in Obtaining the axial length La of the inlet-stage moving rotor blade in Since the axial length of the rotor blade comprises the movable blades and the static blades and the gaps between the movable blades and the static blades, the axial length factor L of the rotor blade is inserted r Obtaining the axial length L of the inlet-stage rotor blade gin The method comprises the following steps:
L gin ＝La in ×L r ；
i.e. the axial length L of the rotor blade of the inlet stage is obtained gin ；
Step four, knowing the inner diameter D of the inlet-stage rotor blade according to the characteristics of the equal-inner-diameter axial flow compressor Hin With the inner diameter D of the rotor blade of the outlet stage Hout Equal, the axial length L of the rotor blade of the outlet stage is calculated according to the steps one to three gout And an outlet stage rotor blade outer diameter D Tout ；
Step five, according to the formula:
L＝(L gin +L gout )×N Z /2
in N Z And obtaining the estimated total length dimension L of the equal-diameter axial flow compressor for the number of stages of the equal-diameter axial flow compressor.
2. The method for calculating the size of the equal-diameter axial compressor taking into account the blade mounting angle as recited in claim 1, wherein said step one specifically includes the steps of:
step 11, the inlet stage rotor blade and outlet stage section parameters of the axial flow compressor comprise: inlet stage rotor blade Mach number Ma in Mach number of exit stage rotor blade Ma out The method comprises the steps of carrying out a first treatment on the surface of the Inlet stage rotor blade flow W in The flow of the rotor blade of the outlet stage is W out The method comprises the steps of carrying out a first treatment on the surface of the The total temperature of the inlet-stage rotor blade is T in The total temperature of the rotor blade of the outlet stage is T out The method comprises the steps of carrying out a first treatment on the surface of the The total pressure of the inlet-stage rotor blade is P in The total pressure of the rotor blade of the outlet stage is P out The method comprises the steps of carrying out a first treatment on the surface of the The gas-oil ratio of the inlet-stage rotor blade is f in The gas-oil ratio of the rotor blade at the outlet stage is f out The method comprises the steps of carrying out a first treatment on the surface of the Calculating the area of the inlet-stage rotor blade ring to be A in The area of the ring of the rotor blade at the outlet stage is A out ；
Step 12, inlet stage rotor blade ring area A according to step 11 in And exit stage rotor blade ring area A out And the inlet stage hub ratio HTR of known axial flow compressors in Calculating the outer diameter D of the inlet-stage rotor blade Tin And the inlet stage rotor blade inner diameter D Hin The method comprises the steps of carrying out a first treatment on the surface of the Thereby obtaining the blade height H of the inlet stage rotor blade Bin Inlet stage rotor bladePitch diameter D Min The method comprises the steps of carrying out a first treatment on the surface of the Finally, according to the inlet stage rotor blade aspect ratio AR in Obtaining chord length C of the inlet-stage rotor blade Bin ；
Step 13, according to the first stage pressure ratio Pr of the axial flow compressor 1 Tangential velocity U to tip of inlet stage rotor blade Tin Obtaining the tangential velocity of the blade tip of the inlet-stage rotor blade as U Tin The method comprises the steps of carrying out a first treatment on the surface of the Then according to the section parameters of the inlet-stage rotor blade of the axial-flow compressor, the air flow axial speed U of the inlet-stage rotor blade is calculated Zin 。
3. The method for calculating the size of the equal-diameter axial compressor taking the blade mounting angle into consideration as claimed in claim 2, wherein said step 11 is specifically:
according to the flow continuity equation:
in the method, in the process of the invention,wherein k is an adiabatic index, R is a gas constant, and the value of a speed factor lambda is 0-1, so that the area of an inlet-stage rotor blade ring of the axial flow compressor is calculated to be A in And an exit stage rotor blade ring area A out 。
4. The method for calculating the size of the equal-diameter axial compressor taking the blade mounting angle into consideration as claimed in claim 2, wherein said step 12 is specifically:
step 121, according to the inlet stage ring area A of the axial flow compressor in Hub ratio HTR to inlet stage of axial compressor in From the geometric equation:
calculating the outer diameter D of the inlet stage rotor blade Tin ；
Step 122, according to the formula:
HTR in ＝D Hin /D Tin
obtaining the inner diameter D of the inlet-stage rotor blade of the axial-flow compressor Hin ；
Step 123, according to the inlet stage rotor blade outer diameter D of said axial flow compressor rotor blade Tin And an inlet stage rotor blade inner diameter D Hin The formula is introduced:
H Bin ＝(D Tin -D Hin )/2
D Min ＝(D Tin +D Hin )/2
calculating the blade height H of the inlet stage rotor blade Bin Pitch diameter D of inlet stage rotor blade Min ；
Step 124, according to the obtained inlet stage rotor blade height H Bin And inlet stage rotor blade aspect ratio AR in By the formula:
C Bin ＝H Bin /AR in
calculating chord length C of inlet-stage rotor blade of axial flow compressor Bin 。
5. The method for calculating the size of the equal-diameter axial compressor taking the blade mounting angle into consideration as claimed in claim 2, wherein said step 13 specifically comprises:
step 131, the tangential velocity of the tip of the inlet-stage rotor blade of the axial flow compressor is U Tin The calculation formula is as follows:
U Tin ＝(-398.46+682.61×Pr 1 -100.38×Pr 1 2 )×(T in /288.15) 0.5 ；
wherein Tin is the total temperature, pr of the inlet-stage rotor blade 1 A first stage pressure ratio for the axial flow compressor;
step 132, the formula:
U Zin ＝Ma in ×Cs
wherein: cs is sonic, ma in Is the Mach number of the rotor blade of the inlet stage, and the axial speed U of the air flow of the rotor blade of the inlet stage is obtained Zin 。
6. The method for calculating the size of an equal-diameter axial compressor taking into account the blade mounting angle as claimed in claim 1, wherein said mounting angle a of said inlet stage rotor blade in said step two in The calculation formula of (2) is as follows:
in U Zin For the axial velocity of the air flow of the rotor blades of the inlet stage, U Tin Is the tip tangential velocity of the inlet stage rotor blade.
7. The method for calculating the size of an equal-diameter axial flow compressor taking into account the blade mounting angle as defined in claim 1, wherein said inlet stage moving rotor blade axial length La in said step three in The calculation formula of (2) is as follows:
wherein: a, a in C for the mounting angle of the inlet stage rotor blade Bin Is the chord length of the inlet stage rotor blade.
8. The method for calculating the size of the equal-inner-diameter axial flow compressor taking the blade installation angle into consideration as claimed in any one of claims 1 to 7, wherein the fourth step is specifically calculated according to the steps one to three in sequence: the area of the ring of the rotor blade of the outlet stage is A out Hub ratio HTR of outlet stage rotor blades out Outer diameter D of outlet stage rotor blade Tout Pitch diameter D of outlet stage rotor blade Mout Rotor blade of outlet stageLeaf height H of tablet Bout Aspect ratio AR of outlet stage rotor blade out Chord length C of outlet stage rotor blade Bout Tangential speed U of outlet-stage blade tip Tout Air flow axial velocity U of outlet stage rotor blade Zout The method comprises the steps of carrying out a first treatment on the surface of the Thereby, the mounting angle a of the outlet stage rotor blade is obtained out Axial length L of outlet-stage rotor blade aout The method comprises the steps of carrying out a first treatment on the surface of the Finally, according to the formula:
L gout ＝L aout ×L r ；
obtain the axial length L of the rotor blade of the outlet stage gout 。
9. The method for calculating the size of an equal-diameter axial flow compressor taking into account the blade mounting angle as defined in claim 8, wherein said outlet stage tip tangential velocity U Tout Is calculated as follows:
by the outer diameter D of the inlet stage rotor blades Tin According to the formula:
U Tin ＝(π/60)D Tin N
calculating the rotating speed N of the axial flow compressor, and then according to the formula:
U Tout ＝(π/60)D Tout N
wherein: d (D) Tout Obtaining the tangential velocity U of the tip of the outlet stage for the outer diameter of the outlet stage rotor blade Tout 。
10. The method for calculating the size of an equal-diameter axial compressor taking into account the blade mounting angle as recited in claim 8, wherein said axial compressor has an outlet stage rotor blade to hub ratio HTR out And outer diameter D of the outlet stage rotor blade Tout The specific calculation of (3) is as follows: from the characteristics of the equal-diameter axial-flow compressor, the inner diameter D of the inlet-stage rotor blade can be known Hin With the inner diameter D of the rotor blade of the outlet stage Hout The values of the two are equal to each other,
then according to the outlet stage ring area A of the axial flow compressor out And an outlet stage rotor blade inner diameter D Hout From the geometric equation:
HTR out ＝D Hout /D Tout
calculating an outlet stage rotor blade hub ratio HTR of the axial flow compressor out And outer diameter D of the outlet stage rotor blade Tout 。
CN202111528129.6A 2021-12-14 2021-12-14 Axial flow compressor size calculation method considering blade installation angle Active CN114329771B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202111528129.6A CN114329771B (en) 2021-12-14 2021-12-14 Axial flow compressor size calculation method considering blade installation angle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202111528129.6A CN114329771B (en) 2021-12-14 2021-12-14 Axial flow compressor size calculation method considering blade installation angle

Publications (2)

Publication Number Publication Date
CN114329771A CN114329771A (en) 2022-04-12
CN114329771B true CN114329771B (en) 2024-02-23

Family

ID=81050613

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202111528129.6A Active CN114329771B (en) 2021-12-14 2021-12-14 Axial flow compressor size calculation method considering blade installation angle

Country Status (1)

Country Link
CN (1) CN114329771B (en)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007081817A2 (en) * 2006-01-09 2007-07-19 Sonic Blue Aerospace Electric turbine bypass fan and compressor for hybrid propulsion
CN103244459A (en) * 2013-04-25 2013-08-14 哈尔滨工业大学 Aerodynamic design method of subsonic adsorption type axial compressor

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007081817A2 (en) * 2006-01-09 2007-07-19 Sonic Blue Aerospace Electric turbine bypass fan and compressor for hybrid propulsion
CN103244459A (en) * 2013-04-25 2013-08-14 哈尔滨工业大学 Aerodynamic design method of subsonic adsorption type axial compressor

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
同王刚 ; 唐海龙 ; 陈敏 ; 张丛辉 ; 顾卫群 ; 谭智勇 ; .轴流压气机流道设计方法研究.航空发动机.2015,(05),全文. *
李景银，刘立军，李超俊.轴流压气机特性计算模型的研究.机械工程学报.1997,(02),全文. *

Also Published As

Publication number Publication date
CN114329771A (en) 2022-04-12

Similar Documents

Publication Publication Date Title
US8186963B2 (en) Airfoil shape for compressor inlet guide vane
US20100068045A1 (en) Inlet guide vane
EP2603703A1 (en) Radial diffuser vane for centrifugal compressors
CN109598081B (en) Radial-flow turbine pneumatic optimization method based on data dimension reduction and multi-two-dimensional flow surface
CN106382253B (en) Method for designing model stage and impeller of pipeline compressor with flow coefficient of 0.02
CN109815624A (en) A kind of compressor stability boundaris judgment method for considering inlet total pressure distortion and influencing
Ikeguchi et al. Design and development of a 14-stage axial compressor for industrial gas turbine
EP2546462B1 (en) Hole for rotating component cooling system
CN115186398A (en) Method for determining key angle parameters of inlet guide vane model of axial flow compressor
CN113883093B (en) Low-reaction-force compressor blade design method, movable blade and compressor
CN113074022B (en) Centripetal turbine using axial flow guide vanes
CN114329771B (en) Axial flow compressor size calculation method considering blade installation angle
CN115982892B (en) Blade design method, blade and related equipment
Park et al. Numerical optimization of a stator blade to enhance aerodynamic performance in a transonic fan stage
EP3719257B1 (en) Turbine wheel for turbochargers, turbocharger and method for producing a turbine wheel for turbochargers
CN115906430A (en) Axial flow compressor labyrinth leakage loss prediction method
CN106250644B (en) Dual arc blade profile compressor blade implementation method
CN113221482B (en) Design method for combination of turbine final stage blade and exhaust cylinder
CN115270318A (en) Modeling method for transonic-grade moving blade of axial flow compressor of marine gas turbine
CN113719459A (en) Mixed-flow compressor for hundred thousand-twenty thousand cubic meter grade air separation device
CN113627030A (en) Single-stage compressor amplification modeling method and system
Němec et al. An investigation of a flow field in one and half axial turbine stage
Vanyashov et al. Analysis of the results of experimental studies of a centrifugal compressor with an inlet guide vane
CN109711047A (en) A kind of design method that helium compressor S2 stream interface is pneumatic
CN217582609U (en) Axial flow compressor of cantilever type adjustable stator and aeroengine

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