CN114720145A - Low-pressure turbine performance test method with rectifying blades - Google Patents
Low-pressure turbine performance test method with rectifying blades Download PDFInfo
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- CN114720145A CN114720145A CN202210345042.3A CN202210345042A CN114720145A CN 114720145 A CN114720145 A CN 114720145A CN 202210345042 A CN202210345042 A CN 202210345042A CN 114720145 A CN114720145 A CN 114720145A
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Abstract
The application provides a performance test method for a low-pressure turbine with a rectifying blade, which comprises the following steps: firstly, before a performance recording test of each state point of a turbine, carrying out a low-pressure turbine test piece inlet rectifying blade loss characteristic blowing test, and respectively measuring the radial multipoint total pressure pipe and the circumferential multipoint total pressure rake which are positioned at the front side and the rear side of a rectifying blade and provided with stagnation chambers and the wall surface static pressure at the front side of the rectifying blade to obtain the total pressure loss coefficients of the inlet of the rectifying blade under different inlet Mach numbers; and step two, removing the circumferential multi-point total pressure rake on the rear side of the rectifying blade, obtaining the total pressure on the rear side of the rectifying blade by using the total pressure and the static pressure on the front side of the rectifying blade and the total pressure loss coefficient of the inlet of the rectifying blade obtained before, and carrying out the performance recording test of each state point of the single-stage turbine in a control state. The method can completely avoid the influence of the inserted probe on the turbine inlet flow field, and has higher measurement and test precision.
Description
Technical Field
The application belongs to the technical field of gas turbine tests, and particularly relates to a low-pressure turbine performance test method with a rectifying blade.
Background
The low-pressure turbine is a key component of a turbomachine, such as an aircraft engine or a gas turbine, and its aerodynamic performance level directly determines the performance and reliability of the turbomachine. The flow and heat exchange processes inside the turbine part are extremely complex, and the characteristics of the turbine part are difficult to accurately obtain by depending on numerical simulation. Therefore, in the development and optimization process of the low-pressure turbine, the experimental verification has an indispensable important position.
The method for testing the aerodynamic performance of the turbine is based on a similar principle, and the expansion ratio of the total pressure of the inlet and the outlet of the turbine (the ratio of the total pressure of the inlet of a turbine guide blade to the total pressure of the outlet of a turbine rotor) is one of main parameters controlled in the process of testing the turbine. Therefore, the accuracy of the turbine inlet total pressure measurement directly determines the accuracy of the turbine total pressure expansion ratio, and the low-pressure turbine matched with the aircraft engine and the gas turbine is a single-stage turbine, the designed expansion ratio is small (about 1.7-2.0), and the minimum measurement deviation of the inlet total pressure brings great errors to the overall performance evaluation of the turbine.
For a single-stage low-pressure turbine aerodynamic performance test, because the upstream high-pressure turbine exists, the inlet airflow of the low-pressure turbine is generally non-axial, so in order to simulate the outlet angle of the high-pressure turbine in the test, a row of rectifying blades are generally arranged at the inlet of the low-pressure turbine, and the main flow passage layout of a low-pressure turbine test piece 10 with rectifying blades is shown in fig. 1, and sequentially comprises a test piece inlet 11, rectifying blades 12, a turbine inlet 13, turbine guide blades 14, turbine rotor blades 15 and a turbine outlet 16.
In the performance test of the low-pressure turbine with the rectifying blades in the prior art, the method for measuring the total pressure at the inlet of the turbine mainly comprises the following two methods:
1) neglecting the influence of the rectifying blades 12 on the total pressure, the total pressure directly measured by a radial multipoint total pressure pipe 17 at the front straight section of the rectifying blades 12 represents the total pressure at the turbine inlet, the form of the radial multipoint total pressure pipe 17 is shown in fig. 2, and the tail end of the radial multipoint total pressure pipe 17 is provided with a stagnation chamber 172 and a radially arranged pressure leading pipe 171. In the method, due to the existence of the rectifying blades 12, a certain loss is generated after the gas flows through the rectifying blades 12, the front and rear total pressures of the rectifying blades 12 are different, and the specific loss is greatly different due to different design difficulties. Especially for a turbine with a small expansion ratio, the influence of the rectifying blades 12 is directly ignored, and the total pressure of the inlet straight section of the test piece is not accurate as the total pressure of the inlet of the turbine, so that the turbine efficiency evaluation is greatly influenced. For example, the total pressure loss coefficient of the rectifying blades is 0.985, the turbine design expansion ratio is 1.8, and the deviation of the loss and the turbine efficiency obtained without considering the loss is nearly 1.1 percentage points.
2) Radial multipoint total pressure pipes 17 are uniformly distributed behind the rectifying blades 12 to directly measure the total pressure at the inlet of the turbine. In the method, the main purpose of the rectifying blades 12 is to change the air flow angle at the inlet of the turbine test piece, the distance between the rectifying blades 12 and the turbine guide blades 14 is small, the requirement of the length of a straight section at the inlet of the turbine cannot be met, the outlet of the rectifying blades 12 has strong three-dimensional characteristics (such as trails and the like), and the total pressure obtained by using a radial multipoint total pressure pipe directly arranged at the outlet of the rectifying blades 12 is also very inaccurate. For example, the total pressure of a certain radial height at the outlet of the rectifying blade obtained by two measurement modes of a certain test total pressure pipe and a total pressure rake is shown in fig. 3, the measurement deviation of the two is close to 0.5%, and the total pressure rake can obviously represent the flow field characteristics of the section.
Neither of the above two methods does not take into account the large influence of the flow straightener blades on the total pressure measurement at the turbine inlet, so that a low pressure turbine performance test method with flow straightener blades is required to overcome the above problems.
Disclosure of Invention
The application aims to provide a low-pressure turbine performance test method with rectifying blades, so as to solve or reduce at least one problem in the background art.
The technical scheme of the application is as follows: a method for testing performance of a low-pressure turbine with a rectifying blade comprises the following steps:
firstly, before a performance recording test of each state point of a turbine, carrying out a low-pressure turbine test piece inlet rectifying blade loss characteristic blowing test, and respectively measuring the radial multipoint total pressure pipe and the circumferential multipoint total pressure rake which are positioned at the front side and the rear side of a rectifying blade and provided with stagnation chambers and the wall surface static pressure at the front side of the rectifying blade to obtain the total pressure loss coefficients of the inlet of the rectifying blade under different inlet Mach numbers;
and step two, removing the circumferential multi-point total pressure rake on the rear side of the rectifying blade, obtaining the total pressure on the rear side of the rectifying blade by using the total pressure and the static pressure on the front side of the rectifying blade and the total pressure loss coefficient of the inlet of the rectifying blade obtained before, and carrying out the performance recording test of each state point of the single-stage turbine in a control state.
Further, the first step specifically includes:
step 1.1, arranging a radial multi-point total pressure pipe at a test piece inlet of a low-pressure turbine test piece to measure inlet total pressure P of a rectifying blade0t；
Step 1.2, arranging a plurality of wall surface static pressure measuring points on the inner wall surface and the outer wall surface of the inlet of the low-pressure turbine test piece along the circumferential direction so as to measure the wall surface static pressure P of the inlet of the rectifying blade0s；
Step 1.3, according to the total inlet pressure P of the measured rectifying blades0tAnd wall static pressure P0sObtaining the inlet Mach number M of the low-pressure turbine test piece by constructing a relational expression0；
Step 1.4, arranging a circumferential multi-point total pressure rake at a plurality of radial positions between the rectifying blades and the turbine guide blades, wherein the circumferential multi-point total pressure rake is provided with a plurality of pressure guide small pipes in the circumferential direction, and acquiring turbine inlet total pressure P containing wake features of the upstream rectifying blades through the plurality of pressure guide small pipes1t；
Step 1.5, carrying out a turbine test piece blowing test before a turbine performance recording test, and fitting by collecting data of low-pressure turbine test piece inlet Mach number and total pressure recovery coefficient to obtain a relation sigma f (M) of total pressure recovery coefficient of inlet and outlet of a rectifying blade and test piece inlet Mach number0)。
Furthermore, the inlet of the test piece is a straight section, and the total inlet pressure of the rectifying blade can be measured by arranging the radial multipoint total pressure pipe at the inlet of the test piece of the straight section.
Further, the inlet total pressure P of the rectifying blade0tAnd wall static pressure P0sThe Mach number M of an inlet of a low-pressure turbine test piece0The following relationship is satisfied:
in the formula, k is a coefficient.
Further, the radial arrangement position of the circumferential multipoint total pressure rake is more than one time of the grid pitch of the rectifying blades.
Further, the second step specifically includes:
step 2.1, dismantling the circumferential multi-point total pressure rake behind the rectifying blade in a turbine performance recording test, and measuring the inlet total pressure P of a low-pressure turbine test piece0tStatic wall pressure P0sCombining a relation sigma f (M) obtained in a low-pressure turbine test piece blowing test0) To obtain the total pressure P at the inlet of the turbine1tRelation P of1t＝f(P0t,M0)；
Step 2.2, obtaining the total pressure P of the turbine inlet1tControlling the test state of the turbine and recording the total characteristics of the turbine;
step 2.3, measuring total pressure P at turbine outlet2tThrough the total pressure ratio P of the inlet and the outlet of the turbine1t/P2tTurbine performance is obtained.
According to the method, the circumferential measurement range of the total pressure rake is larger than 1 time of the pitch of the rectifying blades, so that the obtained total pressure can contain wake characteristics of the rectifying blades. Compared with a radial multipoint sleeved total pressure pipe testing method which cannot consider wake effect, the accuracy of total pressure of an outlet of a rectifying blade obtained by the total pressure rakes arranged at a plurality of radial positions is higher; in addition, any inserted test probe is not required to be arranged between the rectifying blade and the turbine guider during the turbine performance recording test, so that the influence of the inserted probe on the turbine inlet flow field can be completely avoided, and the measurement and test precision is higher.
Drawings
In order to more clearly illustrate the technical solutions provided in the present application, the drawings will be briefly described below. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic view of a low pressure turbine test piece with fairing blades of a typical configuration.
Fig. 2 is a schematic view of a radial multipoint jacketed total pressure pipe used in the prior art.
FIG. 3 is a schematic diagram comparing the measurement results of single radial height of the total pressure pipe and the total pressure rake.
FIG. 4 is a flow chart of a low pressure turbine performance testing method of the present application.
Fig. 5 is a schematic view of a multipoint total pressure rake structure in the present application.
FIG. 6 is a loss characteristic of a fairing blade in an embodiment of the present application.
Reference numerals:
10-low pressure turbine test piece
11-test piece inlet
12-rectifying blade
13-turbine inlet
14-turbine guide vane
15-turbine rotor blade
16-turbine outlet
17-radial multipoint total pressure pipe
18-circumferential multipoint total pressure target
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
The problem of take the low pressure turbine test piece turbine import of fairing blade to always press the inaccurate measurement is aimed at to the low pressure turbine test piece turbine that this application aims at solving to take fairing blade to always press the measurement accuracy of expansion ratio is thereby improved.
For the problem that the rectifying blades influence the total pressure measurement at the inlet of the turbine in the performance test of the low-pressure turbine with the rectifying blades, the method provided by the application accurately obtains the total pressure at the inlet of the turbine by combining the total pressure measurement at the inlet of the test piece with the loss characteristic of the rectifying blades, and the method comprises the following steps:
firstly, before a performance recording test of each state point of a single-stage turbine, carrying out a blowing test of loss characteristics of inlet rectifying blades of a low-pressure turbine test piece, and measuring the total pressure of inlets of the rectifying blades under different inlet Mach numbers by utilizing a radial multipoint total pressure pipe and a circumferential multipoint total pressure rake which are respectively positioned at the rear side of the front side of the rectifying blades and provided with a stagnation chamber and wall static pressure at the front side of the rectifying blades;
and step two, removing the circumferential multi-point total pressure rake on the rear side of the rectifying blade to avoid the influence of the circumferential multi-point total pressure rake on the performance of the turbine, reversely solving the total pressure of the turbine inlet on the rear side of the rectifying blade by using the total pressure and the static pressure on the front side of the rectifying blade and the previously obtained total pressure loss coefficient of the inlet of the rectifying blade, and carrying out the performance recording test of each state point of the single-stage turbine according to the control state.
The method comprises the following specific steps:
step 1.1, arranging a radial multipoint total pressure pipe 17 at a test piece inlet 11 of a low-pressure turbine test piece 10 to measure inlet total pressure P of a rectifying blade 120t。
In general, the inlet 11 of the test piece is a straight section meeting the specification requirement, and the total inlet pressure of the rectifying blades 12 can be accurately measured by arranging the radial multipoint total pressure pipe 17 on the straight section.
Step 1.2, arranging a plurality of wall static pressure measuring points on the inner wall surface and the outer wall surface of the inlet 11 of the test piece along the circumferential direction, and accurately measuring the wall static pressure P at the inlet of the rectifying blade 120s。
Step 1.3, constructing inlet total pressure P of low-pressure turbine test piece 100tStatic wall pressure P0sThe inlet Mach number M of the low-pressure turbine test piece 100According to the measured total inlet pressure P of the low-pressure turbine test piece 100tAnd wall static pressure P0sCalculating to obtain the inlet Mach number M of the low-pressure turbine test piece 100。
Wherein the inlet total pressure P of the constructed low-pressure turbine test piece 100tStatic wall pressure P0sThe inlet Mach number M of the low-pressure turbine test piece 100The relation of (A) is as follows:
Step 1.4, arranging circumferential multi-point total pressure rakes 18 with the grid pitch being more than one time of the rectifying blades 12 at a plurality of radial positions between the rectifying blades 12 and the turbine guide blades 14, wherein the structure of the circumferential multi-point total pressure rakes 18 is shown in fig. 4, the circumferential multi-point total pressure rakes 18 are provided with a plurality of pressure guide small pipes 181 in the circumferential direction, and the plurality of pressure guide small pipes 182 are converged by target bodies 182 and then extend out from radial pipes 183, so that the turbine inlet total pressure P containing the wake characteristic of the upstream rectifying blade 12 can be accurately obtained1t。
Step 1.5, total pressure recovery coefficient sigma of blade cascade of the rectifying blades 12 is P0t/P1tMach number M of the test piece inlet 110Satisfying a certain fixed relationship, the turbine test piece blowing test is performed before the turbine performance recording test, so that the relational expression σ of the inlet total pressure recovery coefficient of the rectifying blade 12 and the test piece inlet mach number is f (M)0)。
As shown in fig. 5, in the embodiment of the present application, a schematic diagram of the relationship between the collection point and the fitting point of the test piece inlet mach number and the total pressure recovery coefficient is obtained, and a relational expression between the total pressure recovery coefficient of the inlet and the outlet of the rectifying blade 12 and the test piece inlet mach number may be obtained through fitting the collection point data.
Step 2.1, because the windward area of the circumferential multi-point total pressure rake 18 is larger than that of the radial multi-point total pressure pipe 17 and the circumferential width is larger, the performance of the downstream turbine guide blade 14 (also called a turbine guide) can be influenced by the existence of the circumferential multi-point total pressure rake 18, so that uncertainty is brought to the performance of a low-pressure turbine, and therefore the circumferential multi-point total pressure rake 18 on the rear side of the rectifying blade 12 is removed in a turbine performance recording test.
In the process of recording the performance of the turbine, the total inlet pressure P of the turbine test piece 10 is measured0tStatic wall pressure P0sCombining a relation between the inlet total pressure recovery coefficient of the rectifying blade 12 obtained in the low-pressure turbine test piece blowing test and the test piece inlet Mach number, wherein sigma is f (M)0) The relation P can be obtained1t＝f(P0t,M0) The total pressure P at the inlet of the turbine can be accurately obtained1t。
Step 2.2, according to the total pressure P of the turbine inlet obtained in the step 2.11tAnd controlling the turbine test state and recording the overall characteristics of the turbine.
2.3, the turbine performance is determined by the total pressure ratio P of the inlet and the outlet of the turbine1t/P2tIs evaluated, wherein the total turbine outlet pressure P2tCan be measured directly.
According to the method, the circumferential measurement range of the total pressure rake is larger than 1 time of the pitch of the rectifying blades, so that the obtained total pressure can contain wake characteristics of the rectifying blades. Compared with a radial multipoint sleeved total pressure pipe testing method which cannot consider wake effect, the accuracy of total pressure of an outlet of a rectifying blade obtained by the total pressure rakes arranged at a plurality of radial positions is higher; in addition, any inserted test probe is not required to be arranged between the rectifying blade and the turbine guider during the turbine performance recording test, so that the influence of the inserted probe on the turbine inlet flow field can be completely avoided, and the measurement and test precision is higher.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A performance test method for a low-pressure turbine with a rectifying blade is characterized by comprising the following steps:
firstly, before a performance recording test of each state point of a turbine, carrying out a low-pressure turbine test piece inlet rectifying blade loss characteristic blowing test, and respectively measuring the radial multipoint total pressure pipe and the circumferential multipoint total pressure rake which are positioned at the front side and the rear side of a rectifying blade and provided with stagnation chambers and the wall surface static pressure at the front side of the rectifying blade to obtain the total pressure loss coefficients of the inlet of the rectifying blade under different inlet Mach numbers;
and step two, removing the circumferential multi-point total pressure rake on the rear side of the rectifying blade, obtaining the total pressure on the rear side of the rectifying blade by using the total pressure and the static pressure on the front side of the rectifying blade and the total pressure loss coefficient of the inlet of the rectifying blade obtained before, and carrying out the performance recording test of each state point of the single-stage turbine in a control state.
2. The method for testing the performance of the low-pressure turbine with the rectifying blades as claimed in claim 1, wherein the first step specifically comprises the following steps:
step 1.1, arranging a radial multi-point total pressure pipe at a test piece inlet of a low-pressure turbine test piece to measure inlet total pressure P of a rectifying blade0t；
Step 1.2, arranging a plurality of wall surface static pressure measuring points on the inner wall surface and the outer wall surface of the inlet of the low-pressure turbine test piece along the circumferential direction so as to measure the wall surface static pressure P of the inlet of the rectifying blade0s；
Step 1.3, according to the total inlet pressure P of the measured rectifying blades0tAnd wall static pressure P0sObtaining the inlet Mach number M of the low-pressure turbine test piece by constructing a relational expression0；
Step 1.4, arranging a circumferential multi-point total pressure rake at a plurality of radial positions between the rectifying blades and the turbine guide blades, wherein the circumferential multi-point total pressure rake is provided with a plurality of pressure guide small pipes in the circumferential direction, and acquiring turbine inlet total pressure P containing wake features of the upstream rectifying blades through the plurality of pressure guide small pipes1t；
Step 1.5, carrying out a turbine test piece blowing test before a turbine performance recording test, and fitting by collecting data of low-pressure turbine test piece inlet Mach number and total pressure recovery coefficient to obtain a relation sigma f (M) of total pressure recovery coefficient of inlet and outlet of a rectifying blade and test piece inlet Mach number0)。
3. The method for testing the performance of the low-pressure turbine with the rectifying blades as claimed in claim 2, wherein the test piece inlet is a straight section, and the total inlet pressure of the rectifying blades can be measured by arranging a radial multipoint total pressure pipe at the test piece inlet of the straight section.
4. The method of claim 2 for testing the performance of a low pressure turbine with straightening vanesCharacterized in that the inlet total pressure P of the rectifying blade0tAnd wall static pressure P0sThe Mach number M of an inlet of a low-pressure turbine test piece0The following relationship is satisfied:
in the formula, k is a coefficient.
5. The method for testing the performance of the low-pressure turbine with the rectifying blades as claimed in claim 2, wherein the radial arrangement position of the circumferential multi-point total pressure rake is more than one time of the grid pitch of the rectifying blades.
6. The method for testing the performance of the low-pressure turbine with the rectifying blades as claimed in claim 1, wherein the second step specifically comprises the following steps:
step 2.1, dismantling the circumferential multi-point total pressure rake behind the rectifying blade in a turbine performance recording test, and measuring the inlet total pressure P of a low-pressure turbine test piece0tWall static pressure P0sCombining a relation sigma f (M) obtained in a low-pressure turbine test piece blowing test0) To obtain the total pressure P at the inlet of the turbine1tRelation P of1t＝f(P0t,M0)；
Step 2.2, obtaining the total pressure P of the turbine inlet1tControlling the test state of the turbine and recording the total characteristics of the turbine;
step 2.3, measuring total pressure P at turbine outlet2tThrough the total pressure ratio P of the inlet and the outlet of the turbine1t/P2tTurbine performance is obtained.
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| CN115356115A (en) * | 2022-10-24 | 2022-11-18 | 中国航发四川燃气涡轮研究院 | Layout method for mainstream flow field fine test in core machine environment |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115356115A (en) * | 2022-10-24 | 2022-11-18 | 中国航发四川燃气涡轮研究院 | Layout method for mainstream flow field fine test in core machine environment |
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