CN112685967A - Design method for circumferential groove type treatment casing of compressor of ship gas turbine - Google Patents
Design method for circumferential groove type treatment casing of compressor of ship gas turbine Download PDFInfo
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Abstract
The invention aims to provide a design method of a circumferential groove type processing casing of a gas compressor of a ship gas turbine, which comprises the steps of selecting typical working conditions according to a pneumatic design result of the gas compressor and obtaining an axial characteristic position of the circumferential groove type processing casing; extracting an inlet absolute airflow angle and an inlet relative airflow angle at the top of the movable blade at the axial characteristic position of the near surge point under a typical working condition so as to determine the slotting angle of the circumferential slot; determining a gap value between the circumferential grooves; selecting 3 influencing factors of the depth of the circumferential groove, the width of the circumferential groove and the number of the circumferential grooves to design a structural scheme; respectively carrying out numerical calculation on different structural design schemes again to determine an optimal scheme; and finally, performing performance analysis on the optimal scheme under the design working condition, and judging whether the performance of the design point of the scheme reaches the standard or not. The invention is not limited to the axial flow compressor of the ship gas turbine, and is also suitable for the design process of the processing casings of the axial flow compressor of various industrial gas turbines with the processing casings and the axial flow compressor of the aeroengine.
Description
Technical Field
The invention relates to a design method of a gas turbine, in particular to a design method of a gas compressor.
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 casing processing technology is a common technical means for improving the surge margin of the compressor under the non-designed working condition. Since the stability expansion effect of the casing processing is discovered in the sixties of the last century, through more than forty years of research, a plurality of effective casing processing structures are discovered, wherein the circumferential groove type casing processing structure is used as a first discovered casing processing structure form, and the stability expansion effect of the casing processing structure is practically verified on various machine types. With the continuous improvement of the requirement of the ship gas turbine on the low-working-condition surge margin index of the gas compressor, how to quickly and effectively design the circumferential groove type processing casing structure meeting the engineering requirement becomes a problem to be solved urgently. Therefore, a design method of the circumferential groove type treatment casing of the gas compressor of the ship gas turbine needs to be developed, a design technology of the circumferential groove type treatment casing of the gas compressor of the ship gas turbine, which is suitable for engineering design and application and can effectively improve the low-working-condition surge margin of the gas compressor, is formed, and the surge margin of the gas compressor can be really improved.
Disclosure of Invention
The invention aims to provide a design method of a circumferential groove type treatment casing of a gas compressor of a ship gas turbine, which solves the design problem of the circumferential groove type treatment casing of the gas compressor of the ship gas turbine.
The purpose of the invention is realized as follows:
the invention discloses a design method of a circumferential groove type treatment casing of a gas compressor of a ship gas turbine, which is characterized by comprising the following steps of:
(1) selecting a typical working condition of a circumferential groove type treatment casing design: selecting the working condition with the minimum surge margin in all working conditions as a typical working condition according to the pneumatic design result of the compressor;
(2) analyzing the distribution of aerodynamic parameters of a flow field at a near-surge point under a typical working condition, including the distribution of relative total pressure and relative Mach number of a meridian plane;
(3) extracting the inlet absolute airflow angle alpha at the top of the movable blade at the axial characteristic position of the near surge point under the typical working condition1And inlet relative flow angle beta1Absolute inlet flow angle alpha1And inlet relative flow angle beta1The method comprises the steps that the method is obtained through full three-dimensional CFD calculation solving under the design point of the whole gas compressor, and therefore the grooving angle of a circumferential groove is determined;
(4) determining a gap value between the circumferential grooves according to the actual structure of the compressor;
(5) selecting 3 influencing factors of the depth of the circumferential groove, the width of the circumferential groove and the number of the circumferential grooves to design a structural scheme;
(6) respectively carrying out numerical calculation on different structural design schemes to determine an optimal scheme;
(7) performing performance analysis on the optimal scheme under a design working condition, and judging whether the performance of a design point of the scheme reaches the standard or not; and (5) if the standard is not met, returning to the step (5) for redesigning.
The present invention may further comprise:
1. the gap between the circumferential grooves is set to a value of between 3 and 5 mm.
2. And (5) obtaining schemes under different influence factors by adopting an orthogonal experiment method, and performing permutation and combination according to an orthogonal table by using three-factor three-level design to obtain 9 schemes for subsequent design.
3. In the step (6), the solution of a steady single channel is adopted for the structures of the blade channels and the processing case at all levels, the generated grids are all structured grids, and the interface of the grid of the processing case and the grid of the blade channels adopts a complete non-matching connection mode;
in the numerical calculation solution, a multi-block grid partitioning technology is adopted, respective structured grids are generated in a rotor channel, a blade top gap and an anti-surge casing respectively, a close-body grid near a blade adopts an O-shaped grid, front and rear extension sections of the blade adopt H-shaped grids, and a butterfly-shaped grid topological structure is adopted in the blade top gap and a circumferential groove;
when the optimal scheme is selected, the judgment is carried out according to the following three indexes:
comprehensive stability margin improvement:
flow margin improvement amount:
peak efficiency improvement amount:
in the formula: pi*、η*M is total pressure ratio, isentropic heat insulation efficiency and inlet flow, subscript os represents a near stable boundary point of the belt casing processing, and bs represents a near stable boundary point of the solid-wall casing;
and selecting a scheme which has the advantages of improving the stability margin of the gas compressor greatly and reducing the peak efficiency minimally in all schemes as an optimal scheme.
The invention has the advantages that:
1. the design method of the circumferential groove type processing casing of the gas compressor of the ship gas turbine, provided by the invention, provides a quick and effective way for realizing the surge-proof and stability-expanding technology of the gas compressor processing casing; the compressor treatment casing obtained by the invention can effectively improve the surge margin index of the compressor under low working conditions, and provides technical support for solving the bottleneck problem of the ship gas turbine under low working conditions.
2. The design method of the circumferential groove type processing casing of the gas compressor of the ship gas turbine, provided by the invention, can quickly obtain the structural form of the circumferential groove type processing casing with the optimal stability expansion effect, shortens the design process of screening and optimizing a large number of samples through the scheme of combining multiple influence factors of the circumferential groove type processing casing structure, effectively reduces the 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 design method of the circumferential groove type treatment casing of the ship gas turbine compressor is not limited to the axial flow compressor of the ship gas turbine, but also is suitable for the design process of the treatment casings of various industrial gas turbine axial flow compressors and aircraft engine axial flow compressors with the treatment casings.
Drawings
FIG. 1 is a flow chart of the present invention;
FIG. 2 is a schematic diagram of important structural parameters of a circumferential groove type processing casing;
fig. 3 is a three-factor three-level orthogonal experimental table.
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. 1-3, the design method of the circumferential groove type treatment casing of the gas compressor of the ship gas turbine is realized by the following steps:
the method comprises the following steps: typical working conditions of the design of the circumferential groove type processing casing are selected. Selecting the working condition with the minimum surge margin in all working conditions as a typical working condition according to the pneumatic design result of the compressor, wherein the general typical working condition is selected near the working condition with low rotating speed in the compressor;
step two: and analyzing the aerodynamic parameter distribution of the flow field at a near-surge point under typical working conditions, including the relative total pressure and relative Mach number distribution of the meridian plane. The radial velocity in the radial groove induced by the circumferential groove at the top of the blade cuts the leakage flow into a plurality of parts, and simultaneously can suck and blow off low-energy fluid masses in the boundary layer of the blade tip, weaken the development of clearance leakage vortex, and delay stall to achieve the effect of stability expansion; therefore, the positions with the maximum relative total pressure loss and the lower relative Mach number are found out during analysis, and the axial characteristic position of the circumferential groove type processing casing is determined;
step three: extracting the inlet absolute airflow angle alpha at the top of the movable blade at the axial characteristic position of the near surge point under the typical working condition1And inlet relative flow angle beta1Absolute inlet flow angle alpha1And inlet relative flow angle beta1The method can be obtained by full three-dimensional CFD calculation solving under the design point of the whole gas compressor, so as to determine the slotting angle of the circumferential groove;
step four: determining a gap value between the circumferential grooves according to the actual structure of the compressor; according to the past design experience, the gap value between the circumferential grooves is set to be 3-5mm reasonably, and a better stability expanding effect can be achieved;
step five: selecting 3 influencing factors of the depth of the circumferential groove, the width of the circumferential groove and the number of the circumferential grooves to design a structural scheme; the orthogonal experiment method is adopted to obtain schemes under different influence factors, three-factor three-level design is generally used, and permutation and combination are carried out according to an orthogonal table to obtain 9 schemes for subsequent design, so that resource and time consumption caused by three-dimensional CFD calculation in the design process is reduced, and the workload of designers is greatly simplified;
step six: respectively carrying out numerical calculation on different structural design schemes to determine an optimal scheme; the invention adopts the solution of a steady single channel for the structures of all levels of blade channels and processing casings, and the generated grids are all structured grids. The interface of the processor case grid and the blade channel grid adopts a complete non-matching connection mode.
In the numerical calculation solution, a multi-block grid partitioning technology is adopted, and respective structured grids are generated in a rotor channel, a blade tip gap and an anti-surge casing respectively. The close-fitting grids near the blades are O-shaped grids, and the front and rear extension sections of the blades are H-shaped grids. And the blade top gap and the circumferential groove adopt a butterfly-shaped grid topological structure.
When the optimal scheme is selected, the judgment is carried out according to the following three indexes:
comprehensive stability margin improvement:
flow margin improvement amount:
peak efficiency improvement amount:
in the formula: pi*、η*And M is the total pressure ratio, isentropic adiabatic efficiency and inlet flow, respectively. The subscript os indicates the near-stability boundary point for the belt casing process, and bs indicates the near-stability boundary point for the solid-walled casing.
Selecting a scheme which has the advantages of improving the stability margin of the gas compressor greatly and reducing the peak efficiency at the minimum from all schemes as an optimal scheme;
step seven: performing performance analysis on the optimal scheme under a design working condition, and judging whether the performance of a design point of the scheme reaches the standard or not; if not, returning to the step five for redesigning.
The design method of the circumferential groove type treatment casing of the ship gas turbine compressor is not limited to the axial flow compressor of the ship gas turbine, but is also suitable for the design process of the treatment casings of various industrial gas turbine axial flow compressors and aircraft engine axial flow compressors with the treatment casings.
Claims (4)
1. A design method of a circumferential groove type treatment casing of a gas compressor of a ship gas turbine is characterized by comprising the following steps:
(1) selecting a typical working condition of a circumferential groove type treatment casing design: selecting the working condition with the minimum surge margin in all working conditions as a typical working condition according to the pneumatic design result of the compressor;
(2) analyzing the distribution of aerodynamic parameters of a flow field at a near-surge point under a typical working condition, including the distribution of relative total pressure and relative Mach number of a meridian plane;
(3) extracting the inlet absolute airflow angle alpha at the top of the movable blade at the axial characteristic position of the near surge point under the typical working condition1And inlet relative flow angle beta1Absolute inlet flow angle alpha1And inlet relative flow angle beta1The method comprises the steps that the method is obtained through full three-dimensional CFD calculation solving under the design point of the whole gas compressor, and therefore the grooving angle of a circumferential groove is determined;
(4) determining a gap value between the circumferential grooves according to the actual structure of the compressor;
(5) selecting 3 influencing factors of the depth of the circumferential groove, the width of the circumferential groove and the number of the circumferential grooves to design a structural scheme;
(6) respectively carrying out numerical calculation on different structural design schemes to determine an optimal scheme;
(7) performing performance analysis on the optimal scheme under a design working condition, and judging whether the performance of a design point of the scheme reaches the standard or not; and (5) if the standard is not met, returning to the step (5) for redesigning.
2. The design method of the circumferential groove type treatment casing of the ship gas turbine compressor as claimed in claim 1, wherein the circumferential groove type treatment casing comprises the following steps: the gap between the circumferential grooves is set to a value of between 3 and 5 mm.
3. The design method of the circumferential groove type treatment casing of the ship gas turbine compressor as claimed in claim 1, wherein the circumferential groove type treatment casing comprises the following steps: and (5) obtaining schemes under different influence factors by adopting an orthogonal experiment method, and performing permutation and combination according to an orthogonal table by using three-factor three-level design to obtain 9 schemes for subsequent design.
4. The design method of the circumferential groove type treatment casing of the ship gas turbine compressor as claimed in claim 1, wherein the circumferential groove type treatment casing comprises the following steps: in the step (6), the solution of a steady single channel is adopted for the structures of the blade channels and the processing case at all levels, the generated grids are all structured grids, and the interface of the grid of the processing case and the grid of the blade channels adopts a complete non-matching connection mode;
in the numerical calculation solution, a multi-block grid partitioning technology is adopted, respective structured grids are generated in a rotor channel, a blade top gap and an anti-surge casing respectively, a close-body grid near a blade adopts an O-shaped grid, front and rear extension sections of the blade adopt H-shaped grids, and a butterfly-shaped grid topological structure is adopted in the blade top gap and a circumferential groove;
when the optimal scheme is selected, the judgment is carried out according to the following three indexes:
comprehensive stability margin improvement:
flow margin improvement amount:
peak efficiency improvement amount:
in the formula: pi*、η*M is total pressure ratio, isentropic heat insulation efficiency and inlet flow, subscript os represents a near stable boundary point of the belt casing processing, and bs represents a near stable boundary point of the solid-wall casing;
and selecting a scheme which has the advantages of improving the stability margin of the gas compressor greatly and reducing the peak efficiency minimally in all schemes as an optimal scheme.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113417889A (en) * | 2021-07-26 | 2021-09-21 | 中国船舶重工集团公司第七0三研究所 | Circumferential groove type processing casing structure of compressor of ship gas turbine |
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| CN102927053A (en) * | 2012-11-12 | 2013-02-13 | 西安交通大学 | Circumferential groove casing treatment method |
| CN105781623A (en) * | 2016-03-04 | 2016-07-20 | 西安交通大学 | Tie piece structure for reducing turbulent flow losses |
| US20200224675A1 (en) * | 2019-01-10 | 2020-07-16 | General Electric Company | Engine Casing Treatment for Reducing Circumferentially Variable Distortion |
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- 2020-12-22 CN CN202011523714.2A patent/CN112685967A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102927053A (en) * | 2012-11-12 | 2013-02-13 | 西安交通大学 | Circumferential groove casing treatment method |
| CN105781623A (en) * | 2016-03-04 | 2016-07-20 | 西安交通大学 | Tie piece structure for reducing turbulent flow losses |
| US20200224675A1 (en) * | 2019-01-10 | 2020-07-16 | General Electric Company | Engine Casing Treatment for Reducing Circumferentially Variable Distortion |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113417889A (en) * | 2021-07-26 | 2021-09-21 | 中国船舶重工集团公司第七0三研究所 | Circumferential groove type processing casing structure of compressor of ship gas turbine |
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Application publication date: 20210420 |