CN115356027A - High-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance - Google Patents
High-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance Download PDFInfo
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Abstract
The application belongs to the technical field of engine tests, and particularly relates to a high-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance. The method comprises the steps of S1, obtaining the total temperature, the total pressure and the fuel flow of an outlet of the gas compressor, and calculating the air flow of the outlet of the gas compressor, the total temperature of an inlet of the high-pressure turbine and the total pressure of an inlet of the high-pressure turbine; s2, acquiring total temperature of an inlet of the fan, air flow of the inlet of the fan and total temperature of outlets of inner and outer ducts of the fan, and calculating power of a low-pressure shaft of the fan; s3, acquiring the total temperature of the outlet of the low-pressure turbine and the total pressure of the outlet of the low-pressure turbine, and determining the total temperature behind the high-pressure turbine based on the power of a low-pressure shaft of the fan; s4, determining the rear total pressure of the high-pressure turbine based on the rear total temperature of the high-pressure turbine and the efficiency of the low-pressure turbine; and S5, determining the efficiency of the high-pressure turbine based on the total inlet temperature of the high-pressure turbine, the total inlet pressure of the high-pressure turbine, the total rear temperature of the high-pressure turbine and the total rear pressure of the high-pressure turbine. The method and the device can realize the evaluation of the efficiency of the high-pressure turbine under the complete machine state of the aircraft engine.
Description
Technical Field
The application belongs to the technical field of engine tests, and particularly relates to a high-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance.
Background
When an aircraft engine complete machine tests, in order to evaluate the performance of each part, the parts can be tested and modified, but because the high-pressure turbine part works in the environments of high temperature, high pressure and the like, the inlet parameters of the high-pressure turbine are difficult to measure by the existing measuring technology.
At present, for the evaluation of the efficiency of a high-pressure turbine of an aircraft engine in a complete machine state, a high-pressure turbine part test characteristic or a numerical simulation characteristic is generally adopted, and the numerical simulation calculation evaluation is carried out by combining test modification of a fan, an air compressor and the like, but the test of the high-pressure turbine part is difficult to simulate the test inlet condition in the complete machine state, so that the deviation between the part test characteristic and the high-pressure turbine characteristic in the complete machine state can be caused, and the efficiency of the high-pressure turbine under the complete machine condition can not be accurately evaluated. In addition, the efficiency of the high-pressure turbine is obtained by adopting a method of testing and modifying at the inlet and the outlet of the high-pressure turbine, and for the testing and modifying, the measurement errors caused by air leakage, casing deformation and the like due to the opening of the relevant section of the inlet of the high-pressure turbine are difficult to evaluate. Therefore, in order to not influence the complete machine state working condition of the high-pressure turbine, the test modification is not generally carried out at the inlet and the outlet of the high-pressure turbine.
Disclosure of Invention
In order to solve one of the above problems, the present application provides a method and an apparatus for evaluating high-pressure turbine efficiency based on low-pressure shaft power balance, which accurately evaluate the high-pressure turbine efficiency without test modification at the inlet and outlet of the high-pressure turbine.
The application provides a high-pressure turbine efficiency evaluation method based on low-pressure shaft power balance, which mainly comprises the following steps:
s1, acquiring total temperature T of outlet of gas compressor 3 Total pressure P 3 Fuel oil flow w f Calculating the compressor outlet air flow W 3 Total inlet temperature T of high-pressure turbine 4 And total pressure P at the inlet of the high-pressure turbine 4 ；
S2, acquiring total temperature T of an inlet of the fan 1 Fan inlet air flow W 1 Total temperature T of fan culvert outlet 13 And the total temperature T of the fan culvert outlet 23 Calculating the low-pressure shaft power L of the fan f ；
S3, acquiring total temperature T of the outlet of the low-pressure turbine 6 And a low pressure turbine outlet total pressure P 6 Based on low-pressure shaft power L of the fan f Determining a high pressure turbine rear total temperature T 5 ；
Step S4, based on total temperature T after high-pressure turbine 5 Determining the rear total pressure P of the high-pressure turbine together with the efficiency of the low-pressure turbine 5 ；
Step S5, based on total inlet temperature T of the high-pressure turbine 4 Total pressure P at inlet of high-pressure turbine 4 High pressure turbine rear total temperature T 5 And total pressure P behind high-pressure turbine 5 A high pressure turbine efficiency is determined.
Preferably, in step S2, the low-pressure shaft power L of the fan is calculated f The method comprises the following steps:
s21, determining total temperature T of the fan inlet through a pneumatic parameter table respectively 1 Corresponding enthalpy value, total temperature T of fan connotation outlet 13 Corresponding enthalpy value and total temperature T of fan culvert outlet 23 The corresponding enthalpy value;
step S22, based on fan inlet air flow W 1 Compressor outlet air flow W 3 And calculating the low-pressure shaft power L of the fan according to the enthalpy values f 。
Preferably, in step S3, the high-pressure turbine rear total temperature T is determined 5 The method comprises the following steps:
step S31, determining total temperature T of outlet of low-pressure turbine through pneumatic parameter table 6 The corresponding enthalpy value;
step S32, low-pressure shaft power L based on fan f Compressor outlet air flow W 3 And total low pressure turbine outlet temperature T 6 Corresponding enthalpy value determining total temperature T after high-pressure turbine 5 The corresponding enthalpy value;
step S33, determining the total temperature T after the high-pressure turbine through a pneumatic parameter table 5 。
Preferably, in step S4, the low-pressure turbine efficiency is obtained by a component test of the low-pressure turbine.
The second aspect of the present application provides a high-pressure turbine efficiency evaluation device based on low-pressure shaft power balance, which mainly includes:
a high-pressure turbine inlet parameter calculation module for obtaining the total temperature T of the outlet of the compressor 3 Total pressure P 3 Fuel oil flow w f Calculating the compressor outlet air flow W 3 Total inlet temperature T of high-pressure turbine 4 And the total pressure P at the inlet of the high-pressure turbine 4 ；
A fan low pressure shaft power calculation module for obtaining the total temperature T of the fan inlet 1 Fan inlet air flow W 1 Total temperature T of fan culvert outlet 13 And total temperature T of fan culvert outlet 23 Calculating the low-pressure shaft power L of the fan f ；
A high-pressure turbine rear total temperature calculation module for acquiring low-pressure turbine outlet total temperature T 6 And a low pressure turbine outlet total pressure P 6 Based on low-pressure shaft power L of the fan f Determining a high pressure turbine rear total temperature T 5 ；
A high-pressure turbine rear total pressure calculation module for calculating the rear total temperature T based on the high-pressure turbine 5 Determining the total pressure P behind the high-pressure turbine according to the efficiency of the low-pressure turbine 5 ；
A high pressure turbine efficiency calculation module for calculating a total inlet temperature T based on the high pressure turbine 4 Total pressure P at inlet of high-pressure turbine 4 High pressure turbine rear total temperature T 5 And the rear total pressure P of the high-pressure turbine 5 A high pressure turbine efficiency is determined.
Preferably, the fan low-pressure shaft power calculation module includes:
a first enthalpy value table look-up unit for determining the total temperature T of the fan inlet by the pneumatic parameter table 1 Corresponding enthalpy value, total temperature T of fan culvert outlet 13 Corresponding enthalpy value and total temperature T of fan culvert outlet 23 The corresponding enthalpy value;
a fan low-pressure shaft power calculation unit for calculating a fan low-pressure shaft power based on a fan inlet air flow W 1 Compressor outlet air flow W 3 And calculating the low-pressure shaft power L of the fan according to the enthalpy values f 。
Preferably, the high-pressure turbine rear total temperature calculation module includes:
a second enthalpy value table look-up unit for determining the total outlet temperature T of the low pressure turbine through a pneumatic parameter table 6 The corresponding enthalpy value;
low pressure shaft balance calculation unit for low pressure shaft power L based on fan f Compressor outlet air flow W 3 And total low pressure turbine outlet temperature T 6 Corresponding enthalpy value determining the total temperature T after the high-pressure turbine 5 The corresponding enthalpy value;
a third enthalpy value table look-up unit for determining the total temperature T after the high pressure turbine by a pneumatic parameter table 5 。
Preferably, in the high-pressure turbine post-total pressure calculation module, the low-pressure turbine efficiency is obtained by a component test of a low-pressure turbine.
The method and the device can realize the evaluation of the efficiency of the high-pressure turbine under the complete machine state of the aircraft engine.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of the present application of a method for estimating high pressure turbine efficiency based on low pressure shaft power balancing.
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 accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
In a first aspect, the present application provides a method for evaluating efficiency of a high-pressure turbine based on low-pressure shaft power balance, as shown in fig. 1, the method mainly includes:
s1, acquiring total temperature T of outlet of gas compressor 3 Total pressure P 3 Fuel oil flow w f Calculating the compressor outlet air flow W 3 Total inlet temperature T of high-pressure turbine 4 And total pressure P at the inlet of the high-pressure turbine 4 。
In the step, according to formulas (1) to (3), a compressor outlet air flow W can be calculated by solving a unary nonlinear equation system through a Newton-Raphson method 3 Total inlet temperature T of high-pressure turbine 4 And the total pressure P at the inlet of the high-pressure turbine 4 ；
P 4 ＝σ b P 3 (2)
Wherein: eta b For combustion efficiency, it can be obtained according to combustion chamber component tests; sigma b The coefficient of recovery for the total pressure of the combustion chamber can be obtained according to the efficiency of combustion chamber components; k g Is a gas flow coefficient according to T 4 And
checking a gas characteristic table and calculating; a. The t,hpt The high pressure turbine nozzle throat area is obtained from a part delivery test.
S2, acquiring total temperature T1 of a fan inlet, air flow W1 of the fan inlet, total temperature T13 of a fan culvert outlet and total temperature T23 of a fan culvert outlet, and calculating low-pressure shaft power L of the fan f 。
In some alternative embodiments, in step S2, the fan low-pressure shaft power L is calculated f The method comprises the following steps:
step S21, determining total temperature T of the fan inlet through a pneumatic parameter table respectively 1 Corresponding enthalpy value, total temperature T of fan connotation outlet 13 Corresponding enthalpy value and fanTotal temperature T of culvert outlet 23 The corresponding enthalpy value;
step S22, based on fan inlet air flow W 1 Compressor outlet air flow W 3 And calculating the low-pressure shaft power L of the fan according to the enthalpy values f . Namely, the low-pressure shaft power L of the fan is calculated according to the formula (4) f ：
L f ＝(W 1 -W 3 )ha(T 13 )+W 3 ha(T 23 )-W 1 ha(T 1 ) (4)
Wherein ha (T) x ) Is the gas temperature T under the unit flow x The enthalpy value can be obtained by checking the pneumatic parameter table.
S3, acquiring total temperature T of an outlet of the low-pressure turbine 6 And the total pressure P at the outlet of the low-pressure turbine 6 Based on low-pressure shaft power L of the fan f Determining a high pressure turbine rear total temperature T 5 。
In some alternative embodiments, in step S3, a high pressure post-turbine total temperature T is determined 5 The method comprises the following steps:
step S31, determining total temperature T of outlet of low-pressure turbine through pneumatic parameter table 6 The corresponding enthalpy value;
step S32, based on low-pressure shaft power L of the fan f Compressor outlet air flow W 3 And total low pressure turbine outlet temperature T 6 Corresponding enthalpy value determining the total temperature T after the high-pressure turbine 5 The corresponding enthalpy value;
step S33, determining the total temperature T after the high-pressure turbine through a pneumatic parameter table 5 。
In step S32, the total temperature T after the high-pressure turbine is determined according to the low-pressure shaft power balance (5) 5 Corresponding enthalpy values:
L f /η ml ＝W 3 ×ha(T 5 )-W 3 ×ha(T 6 ) (5)
wherein eta is ml The mechanical efficiency for the low pressure shaft is given empirically.
Step S4, based on the total temperature T after the high-pressure turbine 5 Determining the total pressure P behind the high-pressure turbine according to the efficiency of the low-pressure turbine 5 。
The step isIn the step, according to the formula (6), the total pressure P after the high-pressure turbine is obtained through calculation 5 ；
Wherein k is g The gas constant of the fuel gas is generally 1.3; eta TL For low pressure turbine efficiency, in some alternative embodiments, the low pressure turbine efficiency is obtained by component testing of the low pressure turbine.
Step S5, based on total inlet temperature T of the high-pressure turbine 4 Total pressure P at inlet of high-pressure turbine 4 High pressure turbine rear total temperature T 5 And total pressure P behind high-pressure turbine 5 A high pressure turbine efficiency is determined.
In the step, according to a formula (7), calculating to obtain the efficiency of the high-pressure turbine;
this application can be under the unchangeable condition of high-pressure turbine operational environment under guaranteeing complete machine state, under the condition that the high-pressure turbine does not test the repacking promptly, through the test repacking result of other parts, comparatively accurate aassessment goes out high-pressure turbine efficiency. The test modification of other parts mainly refers to improvement of the whole machine by setting a temperature or pressure sensor to measure corresponding parameters during the acquisition of the parameters in the steps S1 to S3. The method specifically comprises the following steps:
a) To calculate the low-pressure shaft power, the total temperature T of the fan inlet is required 1 Total pressure P 1 Inlet air flow W 1 And total temperature T of fan inner/outer culvert outlet 13 /T 23 Total pressure P 13 /P 23 Testing is carried out;
b) In order to evaluate the total inlet temperature T of the high-pressure turbine 4 Total pressure P 4 And compressor outlet air flow W 3 The total temperature T of the outlet of the compressor is required 3 Total pressure P 3 Fuel oil flow rate w f Testing is carried out;
c) In order to estimate the total outlet temperature T of the high-pressure turbine 5 And total pressure P 5 Total outlet temperature T of the low-pressure turbine 6 And total pressure P 6 And (6) carrying out testing.
The second aspect of the present application provides a high-pressure turbine efficiency evaluation device based on low-pressure shaft power balance corresponding to the above method, which mainly includes:
a high-pressure turbine inlet parameter calculation module for obtaining the total temperature T of the outlet of the compressor 3 Total pressure P 3 Fuel oil flow w f Calculating the compressor outlet air flow W 3 Total inlet temperature T of high-pressure turbine 4 And the total pressure P at the inlet of the high-pressure turbine 4 ；
A fan low-pressure shaft power calculation module for acquiring total temperature T of the fan inlet 1 Fan inlet air flow W 1 Total temperature T of fan culvert outlet 13 And the total temperature T of the fan culvert outlet 23 Calculating the low-pressure shaft power L of the fan f ；
A high-pressure turbine rear total temperature calculation module for obtaining the low-pressure turbine outlet total temperature T 6 And a low pressure turbine outlet total pressure P 6 Based on low-pressure shaft power L of the fan f Determining a high pressure turbine rear total temperature T 5 ；
A high-pressure turbine rear total pressure calculation module for calculating the rear total temperature T based on the high-pressure turbine 5 Determining the rear total pressure P of the high-pressure turbine together with the efficiency of the low-pressure turbine 5 ；
A high pressure turbine efficiency calculation module for calculating the total inlet temperature T based on the high pressure turbine 4 Total pressure P at inlet of high-pressure turbine 4 High pressure turbine rear total temperature T 5 And total pressure P behind high-pressure turbine 5 A high pressure turbine efficiency is determined.
In some alternative embodiments, the fan low spool power calculation module comprises:
a first enthalpy value table look-up unit for determining total temperature T of the fan inlet by pneumatic parameter tables 1 Corresponding enthalpy value, total temperature T of fan connotation outlet 13 Corresponding enthalpy value and total temperature T of fan culvert outlet 23 The corresponding enthalpy value;
fan is lowA pressure shaft power calculation unit for calculating the pressure shaft power based on the fan inlet air flow W 1 Compressor outlet air flow W 3 And calculating the low-pressure shaft power L of the fan according to the enthalpy values f 。
In some alternative embodiments, the high pressure post-turbine total temperature calculation module includes:
a second enthalpy value table look-up unit for determining the total outlet temperature T of the low pressure turbine through a pneumatic parameter table 6 The corresponding enthalpy value;
low pressure shaft balance calculation unit for low pressure shaft power L based on fan f Compressor outlet air flow W 3 And total low pressure turbine outlet temperature T 6 Corresponding enthalpy value determining the total temperature T after the high-pressure turbine 5 The corresponding enthalpy value;
a third enthalpy value table look-up unit for determining the total temperature T after the high pressure turbine by a pneumatic parameter table 5 。
In some optional embodiments, in the high pressure turbine post total pressure calculation module, the low pressure turbine efficiency is obtained by a component test of a low pressure turbine.
Although the present application has been described in detail with respect to the general description and specific embodiments, it will be apparent to those skilled in the art that certain modifications or improvements may be made based on the present application. Accordingly, such modifications and improvements are intended to be within the scope of this invention as claimed.
Claims (8)
1. A high-pressure turbine efficiency evaluation method based on low-pressure shaft power balance is characterized by comprising the following steps:
s1, acquiring total temperature T of outlet of gas compressor 3 Total pressure P 3 Fuel oil flow w f Calculating the compressor outlet air flow W 3 Total inlet temperature T of high-pressure turbine 4 And the total pressure P at the inlet of the high-pressure turbine 4 ；
S2, acquiring total temperature T of an inlet of the fan 1 Fan inlet air flow W 1 Total temperature T of fan culvert outlet 13 And the fan is outTotal mouth temperature T 23 Calculating the low-pressure shaft power L of the fan f ；
S3, acquiring total temperature T of an outlet of the low-pressure turbine 6 And the total pressure P at the outlet of the low-pressure turbine 6 Based on low-pressure shaft power L of the fan f Determining a high pressure turbine rear total temperature T 5 ；
Step S4, based on total temperature T after high-pressure turbine 5 Determining the rear total pressure P of the high-pressure turbine together with the efficiency of the low-pressure turbine 5 ；
Step S5, based on total inlet temperature T of the high-pressure turbine 4 Total pressure P at inlet of high-pressure turbine 4 High pressure turbine rear total temperature T 5 And total pressure P behind high-pressure turbine 5 A high pressure turbine efficiency is determined.
2. The method of claim 1, wherein in step S2, the fan low-pressure shaft power L is calculated f The method comprises the following steps:
s21, determining total temperature T of the fan inlet through a pneumatic parameter table respectively 1 Corresponding enthalpy value, total temperature T of fan culvert outlet 13 Corresponding enthalpy value and total temperature T of fan culvert outlet 23 The corresponding enthalpy value;
step S22, based on the fan inlet air flow W 1 Compressor outlet air flow W 3 And calculating the low-pressure shaft power L of the fan according to the enthalpy values f 。
3. The method for evaluating efficiency of a high pressure turbine based on low pressure shaft power balance as claimed in claim 1, wherein in step S3, a total post high pressure turbine temperature T is determined 5 The method comprises the following steps:
step S31, determining total temperature T of outlet of low-pressure turbine through pneumatic parameter table 6 The corresponding enthalpy value;
step S32, based on low-pressure shaft power L of the fan f Compressor outlet air flow W 3 And total low pressure turbine outlet temperature T 6 Corresponding enthalpy value determining total temperature T after high-pressure turbine 5 The corresponding enthalpy value;
step S33, passing the pneumatic parameter tableDetermining a high pressure turbine rear total temperature T 5 。
4. The method for evaluating the efficiency of a high pressure turbine based on low pressure shaft power balance as claimed in claim 1, wherein the low pressure turbine efficiency is obtained by a component test of a low pressure turbine in step S4.
5. A high pressure turbine efficiency evaluation device based on low pressure shaft power balancing, comprising:
a high-pressure turbine inlet parameter calculation module for obtaining the total temperature T of the outlet of the compressor 3 Total pressure P 3 Fuel oil flow w f Calculating the compressor outlet air flow W 3 Total inlet temperature T of high-pressure turbine 4 And the total pressure P at the inlet of the high-pressure turbine 4 ；
A fan low-pressure shaft power calculation module for acquiring total temperature T of the fan inlet 1 Fan inlet air flow W 1 Total temperature T of fan culvert outlet 13 And total temperature T of fan culvert outlet 23 Calculating the low-pressure shaft power L of the fan f ；
A high-pressure turbine rear total temperature calculation module for obtaining the low-pressure turbine outlet total temperature T 6 And a low pressure turbine outlet total pressure P 6 Based on the low-pressure shaft power L of the fan f Determining a high pressure turbine rear total temperature T 5 ；
A high-pressure turbine rear total pressure calculation module for calculating the rear total temperature T based on the high-pressure turbine 5 Determining the rear total pressure P of the high-pressure turbine together with the efficiency of the low-pressure turbine 5 ；
A high pressure turbine efficiency calculation module for calculating a total inlet temperature T based on the high pressure turbine 4 Total pressure P at inlet of high-pressure turbine 4 High pressure turbine rear total temperature T 5 And the rear total pressure P of the high-pressure turbine 5 A high pressure turbine efficiency is determined.
6. The low-pressure shaft power balancing based high-pressure turbine efficiency assessment device according to claim 5, wherein said fan low-pressure shaft power calculation module comprises:
first enthalpyA value table look-up unit for determining total temperature T of the fan inlet by pneumatic parameter tables 1 Corresponding enthalpy value, total temperature T of fan connotation outlet 13 Corresponding enthalpy value and total temperature T of fan culvert outlet 23 The corresponding enthalpy value;
a fan low pressure shaft power calculation unit for calculating a fan low pressure shaft power based on a fan inlet air flow W 1 Compressor outlet air flow W 3 And calculating the low-pressure shaft power L of the fan according to the enthalpy values f 。
7. The low-pressure shaft power balance-based high-pressure turbine efficiency evaluation device of claim 5, wherein the high-pressure turbine post-total temperature calculation module comprises:
a second enthalpy value table look-up unit for determining the total outlet temperature T of the low-pressure turbine through a pneumatic parameter table 6 The corresponding enthalpy value;
low pressure shaft balance calculation unit for low pressure shaft power L based on fan f Compressor outlet air flow W 3 And total low pressure turbine outlet temperature T 6 Corresponding enthalpy value determining the total temperature T after the high-pressure turbine 5 The corresponding enthalpy value;
a third enthalpy value table look-up unit for determining the total temperature T after the high pressure turbine by a pneumatic parameter table 5 。
8. The low-pressure shaft power balance-based high-pressure turbine efficiency evaluation device as claimed in claim 5, wherein in the high-pressure turbine post-total-pressure calculation module, the low-pressure turbine efficiency is obtained by a component test of a low-pressure turbine.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117147027A (en) * | 2023-11-01 | 2023-12-01 | 哈尔滨工业大学 | Efficiency measurement method and system for micro turbine external sensor of breathing machine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117147027A (en) * | 2023-11-01 | 2023-12-01 | 哈尔滨工业大学 | Efficiency measurement method and system for micro turbine external sensor of breathing machine |
| CN117147027B (en) * | 2023-11-01 | 2024-03-19 | 哈尔滨工业大学 | Efficiency measurement method and system for micro turbine external sensor of breathing machine |
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