CN112487565A - Multi-column rotatable guide/stationary blade power exponent type combined regulation and control rule design method for multistage axial flow compressor of ship gas turbine - Google Patents
Multi-column rotatable guide/stationary blade power exponent type combined regulation and control rule design method for multistage axial flow compressor of ship gas turbine Download PDFInfo
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- CN112487565A CN112487565A CN202011161322.6A CN202011161322A CN112487565A CN 112487565 A CN112487565 A CN 112487565A CN 202011161322 A CN202011161322 A CN 202011161322A CN 112487565 A CN112487565 A CN 112487565A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
Abstract
The invention aims to provide a design method of a multi-column rotatable guide/stationary blade power exponent combined regulation rule of a multistage axial flow compressor of a ship gas turbine, which comprises the steps of extracting pneumatic parameters at the characteristic section position of a first-stage moving blade at an inlet, obtaining the pneumatic parameters at the inlet of the first-stage moving blade at a reduced rotating speed, and further calculating the rotating angle of the rotatable guide blade at the inlet at the reduced rotating speed; then, the rotation angle of each row of rotatable stationary blades in the action process is in a power exponent rule relationship with the rotation angle, and the rotation angle value of each row of rotatable stationary blades is obtained; and respectively calculating the rotation angle of each row of rotatable guide/stationary blades under each characteristic reduced rotation speed to obtain the rotation angle of each row of rotatable guide/stationary blades of the gas compressor under different reduced rotation speeds, thereby designing a multi-row rotatable guide/stationary blade power exponential type combined regulation rule of the gas compressor. The invention can quickly obtain a more ideal multi-row rotatable guide/stationary blade combined regulation and control corner rule and effectively improve the surge margin index of the compressor under low working conditions.
Description
Technical Field
The invention relates to a design method of a gas turbine, in particular to a design method of a gas compressor of a ship gas turbine.
Background
The compressor is one of the most important three core components of the ship gas turbine, and the technical performance and reliability of the compressor directly influence the realization of the safety and economic indexes of the ship gas turbine. The ship gas turbine is required to be forced to operate with wide margin and high efficiency under low working conditions while the performance of a design point is ensured. The operation characteristic under the large-range variable working condition enables the problem of low working condition stability of the gas turbine to be prominent when the gas turbine is used as a ship power system for propulsion or power generation, and the problem often becomes a limiting bottleneck of unit performance, so that higher requirements are provided for the performance and the stability of a ship gas turbine compressor under the non-designed working condition. Therefore, in order to make the ship gas turbine have a wider stable working range and more excellent variable working condition performance, various surge prevention and stability expansion technologies are often needed to be adopted, and the surge margin index of the compressor under a low working condition is improved.
Among various compressor surge-proof and stability-expanding technologies, a rotatable/stationary blade regulation technology is the most common and important technical means for improving the performance of the compressor under the non-design working condition. With the continuous improvement of the requirement of the ship gas turbine on the low-working-condition surge margin index of the gas compressor, the anti-surge and stability-expansion design technology of the rotatable guide/stationary blade of the gas compressor is also continuously developed. Meanwhile, with the gradual increase of the number of the rows of the rotatable guide/stationary blades and the increasing flexibility of the adjustment and control mode of the rotatable guide/stationary blades, the number of samples of the angle combination scheme between the rows of the rotatable guide/stationary blades is increased dramatically, which brings greater difficulty and challenge to the design of the joint adjustment and control corner rule of the multiple rows of the rotatable guide/stationary blades of the compressor.
Disclosure of Invention
The invention aims to provide a rotatable guide/stationary blade anti-surge and stability-expansion design technology of a gas compressor of a ship gas turbine, which can effectively improve the low-working-condition surge margin of the gas compressor, and a multi-row rotatable guide/stationary blade power exponent combined regulation and control rule design method of a multistage axial flow gas compressor of the ship gas turbine, which realizes the improvement of the surge margin of the gas compressor.
The purpose of the invention is realized as follows:
the invention relates to a design method of a multi-column rotatable guide/stationary blade power exponent combined regulation rule of a multistage axial flow compressor of a ship gas turbine, which is characterized by comprising the following steps of:
(1) selecting the position along the average radius of the blade height as a characteristic section for calculating the rotating angle of the rotatable guide/stationary blade;
(2) extracting the pneumatic parameters of the compressor at the position of the characteristic section of the inlet first-stage moving blade at the design point, comprising the following steps: inlet axial velocity C1aPeripheral speed U, inlet absolute airflow angle alpha1And inlet relative flow angle beta1；
(3) The design point of the compressor is used for reducing the rotating speed nnpAnd a reduced speed n of the compressor requiring resolution of the angle of rotation of the rotatable guide/stator vanesnpAcquiring the peripheral speed U' of the characteristic section position of the first-stage moving blade at the reduced rotating speed;
(4) set at the reduced rotation speed nnp' Next, the desired reduced flow value G is adjusted by rotating the rotatable guide/stationary bladenp', combined with compressor design point reduced flow value GnpObtaining the inlet axial velocity C at the position of the characteristic section of the first-stage moving blade at the reduced rotating speed1a′；
(5) Solving for the inlet rotatable guide vane at the reduced rotation speed nnp' the angle of rotation delta alpha at the time, the relative flow angle of the inlet at the position of the characteristic section of the first-stage moving blade is kept constant before and after the rotation of the rotatable guide/stationary blade, namely beta1′＝β1According to the peripheral speed U' and the inlet axial speed C at the position of the characteristic section of the first-stage moving blade at the reduced rotating speed1a' and inlet relative flow angle beta1Acquiring an inlet absolute airflow angle alpha at the characteristic section position of the first-stage moving blade after the rotary guide/stationary blade rotates at the reduced rotating speed1', further obtaining the inlet rotatable guide vanes at the reduced rotation speed nnpAngle of rotation at time Δ α;
(6) taking the obtained inlet rotatable guide vane rotation angle as a reference rotation angle delta alpharefThe rotation angle delta alpha of each row of rotatable stator blades in the action processjObtaining the rotation angle value of each row of rotatable stationary blades in a power exponent rule relationship with the fixed blades;
(7) and respectively calculating the rotation angle of each row of rotatable guide/stationary blades under each characteristic reduced rotation speed according to the steps to obtain the rotation angle of each row of rotatable guide/stationary blades of the gas compressor under different reduced rotation speeds, thereby designing a multi-row rotatable guide/stationary blade power exponent combined regulation rule of the gas compressor.
The present invention may further comprise:
1. the peripheral speed U' is calculated as follows:
2. inlet axial velocity C1aIn the calculation, the influence of the simultaneous action of a plurality of rows of rotatable guide vanes on the combined regulation and control effect of the axial speed of the inlet of the first-stage movable vane is considered and corrected, and the calculation method comprises the following steps:
in the above formula, δcAnd the correction coefficient is the axial speed of the inlet of the movable blade.
3. Inlet absolute airflow angle alpha1' the calculation method is as follows:
further determining the rotational speed n of the rotatable guide vanes at the inletnpThe rotation angle Δ α at' is calculated as follows:
Δα＝α1′-α1。
4. the rotation angle delta alpha of each row of rotatable stator blades in the action processjThe steps of solving the rotation angle value of each row of rotatable stationary blades in relation to the exponential law are as follows:
the power exponent law is calculated as follows:
defining exponent law coefficient P between each row of switchable/stationary vanesj，PjIs calculated by the following formula:
wherein n is an exponential coefficient;
the angle of rotation Delta alpha of each row of rotatable stator blades during operationjAngle delta alpha with reference to the reference datumrefThe relationship between them is calculated as follows:
Δαj＝PjΔαref。
the invention has the advantages that:
1. the design method of the multi-column rotatable guide/stationary blade power exponent combined regulation and control rule of the multistage axial flow compressor of the ship gas turbine provides a quick and effective way for realizing the anti-surge and stability-expansion technology of the multi-column rotatable guide/stationary blade combined regulation and control of the compressor; the multi-row rotatable guide/stationary blade power exponent combined regulation rule of the gas compressor, which is obtained by the invention, can effectively improve the surge margin index of the gas compressor under low working conditions, and provides technical support for solving the bottleneck problem of the low working conditions of the ship gas turbine.
2. The multi-column rotatable guide/stationary blade power exponent type combined regulation and control rule design method provided by the invention can quickly obtain a more ideal multi-column rotatable guide/stationary blade combined regulation and control corner rule, shortens the traditional rotatable guide/stationary blade corner rule design process of screening and optimizing a large number of samples through different angle combination schemes among the multi-column rotatable guide/stationary blades, effectively reduces resource and time consumption caused by a large number of three-dimensional CFD calculations in the design process, simplifies the workload of designers, and is very suitable for engineering design application.
3. The multi-column rotatable guide/stationary blade power exponent combined regulation and control rule design method of the multistage axial flow compressor of the ship gas turbine is not limited to the axial flow compressor of the ship gas turbine, but also is suitable for the rotatable guide/stationary blade corner rule design process of various industrial axial flow compressors with rotatable guide/stationary blades and axial flow compressors of aeroengines.
Drawings
FIG. 1 is a flow chart of the present invention;
FIG. 2 is a diagram illustrating the principle of the design of the corner rule of the rotatable guide vane at the inlet of the compressor and the definition of the aerodynamic parameters.
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
with reference to fig. 1-2, the method for designing the multi-column rotatable guide/stationary blade power exponent type combined regulation rule of the multistage axial flow compressor of the ship gas turbine comprises the following specific steps:
the method comprises the following steps: selecting the position of the average radius along the height of the blade as a characteristic section for calculating the rotating angle of the rotatable/stationary blade, wherein the average radius value can be calculated by adopting an arithmetic mean method or an area weighted mean method;
step two: extracting main pneumatic parameters of a compressor at the characteristic section position of a first-stage moving blade at a design point (all rotatable guide/stationary blade rotation angles are 0 degree at the moment) inlet of the compressor, wherein the main pneumatic parameters comprise: inlet axial velocity C1aPeripheral speed U, inlet absolute airflow angle alpha1And inlet relative flow angle beta1. The pneumatic parameters can be obtained by full three-dimensional CFD calculation solution under the design point of the whole gas compressor, and can also be obtained by quasi three-dimensional through flow design calculation of the gas compressor;
step three: the design point of the compressor is used for reducing the rotating speed nnpAnd a reduced speed n of the compressor requiring resolution of the angle of rotation of the rotatable guide/stator vanesnp'calculating the circumferential speed U' of the first-stage moving blade at the characteristic cross section position at the reduced rotating speed, wherein the calculation method comprises the following steps:
step four: setting a value at the reduced rotation speed nnp' Next, the desired reduced flow value G is adjusted by rotating the rotatable guide/stationary bladenp', combined with compressor design point reduced flow value GnpCalculating the inlet axial velocity C at the position of the characteristic section of the first-stage moving blade at the reduced rotation speed1a'. In the calculation, the influence of the simultaneous action of a plurality of rows of rotatable guide vanes on the combined regulation and control effect of the axial speed of the inlet of the first-stage movable vane is considered and corrected, and the calculation method comprises the following steps:
in the above formula, δcThe correction coefficient of the axial speed of the inlet of the movable blade is related to the total row number N of the rotatable guide/static blades of the compressor, namely:
δc＝f(N)
step five: solving for the inlet rotatable guide vane at the reduced rotation speed nnpAngle of rotation at Δ α. The regulation principle of rotatable stator is through rotatable stator rotation, guarantees that first order moving blade is the relative angle of flow of import under the low operating mode unanimous basically with the design condition, consequently, keeps the relative angle of flow of import of first order moving blade characteristic cross section position department unchangeable around rotatable guide/quiet leaf rotates, promptly:
β1′＝β1
according to the peripheral speed U' and the inlet axial speed C of the first-stage moving blade at the characteristic section position under the reduced rotating speed1a' and inlet relative flow angle beta1' calculating the absolute airflow angle alpha of the inlet at the characteristic section position of the first-stage moving blade after the rotary guide/stationary blade rotates at the reduced rotating speed1', the calculation method is as follows:
further determining the rotational speed n of the rotatable guide vanes at the inletnpThe rotation angle Δ α at' is calculated as follows:
Δα＝α1′-α1
step six: taking the inlet rotatable guide vane rotation angle obtained above as a reference rotation angle delta alpharefNamely:
Δαref＝Δα
the rotation angle delta alpha of each row of rotatable stator blades in the action processjIn relation to its power exponent rule, the power exponent rule is calculated as follows:
defining exponent law coefficient P between each row of switchable/stationary vanesj，PjIs calculated by the following formula:
in the formula, n is an index coefficient, and can be optimally adjusted according to surge margins and efficiency design indexes of different gas compressors and specific performance conditions of the gas compressors. When n is 1, the exponential law becomes a linear law, including:
the angle of rotation Delta alpha of each row of rotatable stator blades during operationjAngle delta alpha with reference to the reference datumrefThe relationship between them is calculated as follows:
Δαj＝PjΔαref
the rotation angle value of each row of rotatable stationary blades can be obtained;
step seven: and by analogy, calculating the rotation angle of each row of rotatable guide/stationary blades under each characteristic reduced rotation speed according to the steps to obtain the rotation angle of each row of rotatable guide/stationary blades of the gas compressor under different reduced rotation speeds, thereby designing a multi-row rotatable guide/stationary blade power exponential type combined regulation rule of the gas compressor.
Claims (5)
1. A multi-column rotatable guide/stationary blade power exponent combined regulation and control rule design method for a multistage axial flow compressor of a ship gas turbine is characterized by comprising the following steps:
(1) selecting the position along the average radius of the blade height as a characteristic section for calculating the rotating angle of the rotatable guide/stationary blade;
(2) extracting the pneumatic parameters of the compressor at the position of the characteristic section of the inlet first-stage moving blade at the design point, comprising the following steps: inlet axial velocity C1aPeripheral speed U, inlet absolute airflow angle alpha1And inlet relative flow angle beta1；
(3) The design point of the compressor is used for reducing the rotating speed nnpAnd a reduced speed n of the compressor requiring resolution of the angle of rotation of the rotatable guide/stator vanesnpAcquiring the peripheral speed U' of the characteristic section position of the first-stage moving blade at the reduced rotating speed;
(4) set at the reduced rotation speed nnp' Next, the desired reduced flow value G is adjusted by rotating the rotatable guide/stationary bladenp', combined with compressor design point reduced flow value GnpObtaining the inlet axial velocity C at the position of the characteristic section of the first-stage moving blade at the reduced rotating speed1a′；
(5) Solving for the inlet rotatable guide vane at the reduced rotation speed nnp' the rotation angle delta alpha at the time keeps the relative airflow angle of an inlet at the position of the characteristic section of the first-stage moving blade unchanged before and after the rotation of the rotatable guide/stationary blade, namely beta1′＝β1According to the peripheral speed U' and the inlet axial speed C at the position of the characteristic section of the first-stage moving blade at the reduced rotating speed1a' and inlet relative flow angle beta1Acquiring an inlet absolute airflow angle alpha at the characteristic section position of the first-stage moving blade after the rotary guide/stationary blade rotates at the reduced rotating speed1', further obtaining the inlet rotatable guide vanes at the reduced rotation speed nnpAngle of rotation at time Δ α;
(6) taking the obtained inlet rotatable guide vane rotation angle as a reference rotation angle delta alpharefThe rotation angle delta alpha of each row of rotatable stationary blades during the operationjIn relation to its exponential law, obtain each columnThe rotating angle value of the rotatable stationary blade;
(7) and respectively calculating the rotation angle of each row of rotatable guide/stationary blades under each characteristic reduced rotation speed according to the steps to obtain the rotation angle of each row of rotatable guide/stationary blades of the gas compressor under different reduced rotation speeds, thereby designing a multi-row rotatable guide/stationary blade power exponent combined regulation rule of the gas compressor.
2. The design method of the multi-column rotatable guide/stationary blade power exponent combined regulation and control law of the multistage axial flow compressor of the marine gas turbine as claimed in claim 1, is characterized in that:
the peripheral speed U' is calculated as follows:
3. the design method of the multi-column rotatable guide/stationary blade power exponent combined regulation and control law of the multistage axial flow compressor of the marine gas turbine as claimed in claim 2, is characterized in that: inlet axial velocity C1aIn the calculation, the influence of the simultaneous action of a plurality of rows of rotatable guide vanes on the combined regulation and control effect of the axial speed of the inlet of the first-stage movable vane is considered and corrected, and the calculation method comprises the following steps:
in the above formula, δcAnd the correction coefficient is the axial speed of the inlet of the movable blade.
4. The design method of the multi-column rotatable guide/stationary blade power exponent combined regulation and control law of the multistage axial flow compressor of the marine gas turbine as claimed in claim 3, wherein the method comprises the following steps: inlet absolute airflow angle alpha1' the calculation method is as follows:
further determining the rotational speed n of the rotatable guide vanes at the inletnpThe rotation angle Δ α at' is calculated as follows:
△α＝α1′-α1。
5. the design method of the multi-column rotatable guide/stationary blade power exponent combined regulation and control law of the multistage axial flow compressor of the marine gas turbine as claimed in claim 4, wherein the method comprises the following steps: the rotation angle delta alpha of each row of rotatable stationary blades in the process of actionjThe steps of solving the rotation angle value of each row of rotatable stationary blades in relation to the exponential law are as follows:
the power exponent law is calculated as follows:
defining exponent law coefficient P between each row of switchable/stationary vanesj，PjIs calculated by the following formula:
wherein n is an exponential coefficient;
the rotation angle Delta alpha of each row of rotatable stationary blades in the action processjAngle Δ α to reference datumrefThe relationship between them is calculated as follows:
△αj＝Pj△αref。
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| WO2022089485A1 (en) * | 2020-10-27 | 2022-05-05 | 中国船舶集团有限公司第七〇三研究所 | Method for determining and adjusting rotation angle of rotatable guide vane, axial flow compressor, and gas turbine |
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