CN115186440B - Pneumatic design method for two-stage high-speed power turbine of marine power generation type gas turbine - Google Patents
Pneumatic design method for two-stage high-speed power turbine of marine power generation type gas turbine Download PDFInfo
- Publication number
- CN115186440B CN115186440B CN202210675151.1A CN202210675151A CN115186440B CN 115186440 B CN115186440 B CN 115186440B CN 202210675151 A CN202210675151 A CN 202210675151A CN 115186440 B CN115186440 B CN 115186440B
- Authority
- CN
- China
- Prior art keywords
- turbine
- power
- power turbine
- stage
- design
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
Abstract
The invention aims to provide a pneumatic design method for a two-stage high-speed power turbine of a marine power generation type gas turbine, which is characterized in that after power turbine design parameters are determined, a power distribution proportionality coefficient, a stage reaction degree and the relative front edge radius of each row of blades are selected as control parameters, and parameterization design of a step-by-step distribution rule is carried out, and a power turbine pneumatic scheme meeting the performance requirement of all working conditions is obtained through one-dimensional pneumatic design of the power turbine, pneumatic performance analysis of the power turbine under typical working conditions and overall performance evaluation of the whole machine under all working conditions. The invention realizes the power distribution and the degree of reaction of each stage and the parameterization and customization of the relative front edge radius of each row of blades by the specific regular setting of individual key control parameters, accelerates the design process and improves the design efficiency. The invention is not only limited to the power turbine of the marine gas turbine, but also applicable to the pneumatic design process of the two-stage power turbine of the industrial gas turbine with wide application range and high requirements on all-condition performance indexes.
Description
Technical Field
The invention relates to a gas turbine design method, in particular to a power turbine design method.
Background
Because the gas turbine has the advantages of high power density, high starting speed and the like, the gas turbine has become the main power of large and medium-sized water surface ships, and the gas turbine or a comprehensive electric propulsion system based on the gas turbine can be used as a ship main engine to greatly improve the performance of the ships. The marine gas turbine has higher performance requirements for wide range of variable operating conditions (0-100%) and operates at low operating conditions for a substantial portion of its life. Meanwhile, the working condition of the ship is frequently changed due to the maneuverability requirement of the ship, and the wide-range variable working condition makes the marine gas turbine very sensitive to the wide-range working characteristic of the power turbine. The marine gas turbine as the prime mover of the comprehensive power system of the ship has new and higher requirements on the pneumatic design and variable working condition characteristics of the power turbine. For the power turbine working at the transverse rotating speed of the marine power generation type gas turbine, the design of the power turbine not only needs to consider the excellent aerodynamic performance in the design working condition, but also has good variable working condition characteristics.
The working characteristics of the power turbine of the marine gas turbine in a wide range of variable working conditions increase the difficulty and complexity of pneumatic design of the power turbine of the marine gas turbine. The traditional turbine pneumatic design method is difficult to meet the design requirement of the wide-working-condition high-efficiency power turbine, the turbine pneumatic design capacity and design level need to be expanded and improved to meet the higher and higher performance index requirement of the marine power generation type gas turbine, and scientific researchers hope to have an advanced design method capable of effectively improving the performance deviation problem of the marine gas turbine high-speed power turbine used for constant-rotation-speed power generation in a time-varying working condition.
Disclosure of Invention
The invention aims to provide a pneumatic design method for a two-stage high-speed power turbine of a marine power generation type gas turbine, which can solve the problem of performance deviation of a high-speed power turbine of the marine gas turbine in a constant-speed power generation time-varying working condition.
The purpose of the invention is realized in the following way:
the invention relates to a pneumatic design method of a two-stage high-speed power turbine of a marine power generation type gas turbine, which is characterized by comprising the following steps of:
(1) Determining power turbine design parameters: determining power turbine design parameters including power turbine inlet conditions, rotating speed, flow, expansion ratio, progression, first stage guide vane inlet size and last stage guide vane outlet size limit according to overall performance parameters of the marine gas turbine design working condition complete machine;
(2) And (3) designing a power turbine through flow: according to the one-dimensional through flow design program of the turbine, the one-dimensional through flow design of the power turbine under the full-load working condition is completed, and the one-dimensional through flow of the power turbine is obtained;
(3) Giving a power distribution proportionality coefficient, a stage reaction degree and a radius distribution rule of each row of blades relative to the front edge, and giving a first stage power and a last stage power distribution proportionality coefficient K of the power turbine according to a decreasing power distribution rule; the first-stage reaction degree omega of the power turbine is given according to the decreasing reaction degree distribution form 1 And final degree of reaction Ω 2 The method comprises the steps of carrying out a first treatment on the surface of the Given movement in a constant relative leading edge radius profileForce turbine row of blades relative to leading edge radius
(4) One-dimensional pneumatic design of a power turbine: adopting a one-dimensional aerodynamic design program of a turbine to complete one-dimensional aerodynamic design of a power turbine under a full-load working condition, obtaining a one-dimensional aerodynamic calculation model of the turbine, judging whether the overall performance design index requirement of the whole machine under the full-load working condition is met or not, if so, continuing to develop the subsequent steps, if not, repeating the steps (2) to (4), adjusting the first-stage power and the last-stage power distribution proportion coefficient K according to a decreasing power distribution rule when the step (3), and adjusting the first-stage reaction degree omega of the power turbine according to a decreasing reaction degree 1 And final degree of reaction Ω 2 Adjusting the relative leading edge radius of each row of blades of the power turbine according to the distribution form of the constant relative leading edge radius
Until the power turbine parameters meet the overall performance design index requirements of the whole machine under the full-load working condition;
(5) Analysis of aerodynamic performance of a power turbine under typical working conditions: based on the one-dimensional aerodynamic calculation model of the power turbine obtained in the step (4), aiming at the unique working characteristics of constant-speed operation of the marine power generation type gas turbine, carrying out one-dimensional aerodynamic performance analysis of the power turbine under the typical working condition under the constant-speed condition to obtain a one-dimensional aerodynamic result of the power turbine under the typical working condition, judging whether the overall performance of the whole machine meets the index requirement of the power turbine under the typical working condition, if the overall performance meets the requirement, continuing to carry out the subsequent steps, and if the overall performance of the whole machine does not meet the requirement, repeating the steps (2) to (5) until the parameters of the power turbine meet the overall performance index requirement of the whole machine under the typical working condition;
(6) Calculating the power turbine characteristics: based on the one-dimensional aerodynamic calculation model of the power turbine obtained in the step (4), carrying out power turbine characteristic calculation by adopting a one-dimensional aerodynamic calculation analysis program of the turbine to obtain turbine characteristic parameters such as turbine efficiency, flow and the like under different rotation speeds and expansion ratio arrangement and combination working states;
(7) Overall performance evaluation of the whole machine under all working conditions: and (3) carrying out complete machine full-working condition matching calculation of the marine power generation type gas turbine by utilizing the turbine characteristic parameters obtained in the step (6), obtaining overall performance parameters such as complete machine full-working condition power, efficiency and the like of the marine power generation type gas turbine, evaluating whether the overall performance parameters meet the design index requirements under the full-working condition, if so, ending the design process, and if not, repeating the steps (2) to (7) until the overall performance parameters meet the design index requirements under the full-working condition.
The invention may further include:
1. the power turbine power split scaling factor described in step (3) is defined as follows:
K=given value, K is more than or equal to 1.0 and less than or equal to 1.5.
2. Degree of reaction Ω of the power turbine in step (3) 1 、Ω 2 The definition is as follows:
Ω 1 given value, 0.35≤Ω 1 ≤0.55；
Ω 2 Given value =0.25.ltoreq.Ω 2 ≤0.5；
Degree of reaction Ω of two-stage power turbine 1 、Ω 2 The relationship is as follows:
Ω 1 ≥Ω 2 。
3. the relative leading edge radius of each row of blades in the step (3)
The relationship with the blade row number i is defined as follows:
the invention has the advantages that:
1. the invention distributes the proportionality coefficient K and the stage reaction degree omega through the power of the power turbine i Relative leading edge radius of each row of blades
The design of the distribution rule realizes the power distribution, the degree of reaction at each level and the parametrization and customization of the radius of each row of blades relative to the front edge, effectively solves the problem of the deviation of the time-varying working condition performance of the traditional marine gas turbine power turbine when the pneumatic design method is used for the constant-rotation-speed power generation power turbine, effectively improves the variable working condition performance of the marine gas turbine power turbine, and obviously widens the high-efficiency working condition. The marine gas turbine designed by the invention has the advantages that the double-stage high speed is realized, the efficiency of the power turbine near the design working point is 0.2% higher than that of the design index, and the efficiency of the power turbine under the working condition of 0.3-0.8 is improved by 0.4% compared with that of the power turbine in the traditional method.
2. The invention can realize the fine design of the pneumatic scheme of the high-speed power turbine of the marine gas turbine, effectively improve the pneumatic design precision of the high-speed power turbine of the marine gas turbine and shorten the design period.
3. The invention is not only limited to the power turbine of the marine gas turbine, but also applicable to the pneumatic design process of the two-stage power turbine of the industrial gas turbine with wide application range and high requirements on all-condition performance indexes.
Drawings
FIG. 1 is a flow chart of the present invention.
Detailed Description
The invention is described in more detail below, by way of example, with reference to the accompanying drawings:
with reference to fig. 1, the pneumatic design method of the two-stage high-speed power turbine of the marine power generation type gas turbine is realized through the following steps:
step one: a power turbine design parameter is determined. Determining power turbine design parameters including power turbine inlet conditions, rotating speed, flow, expansion ratio, progression, first stage guide vane inlet size, last stage movable vane outlet size limit and the like according to overall performance parameters of the marine gas turbine design working conditions (full load working conditions);
step two: and (5) designing a power turbine through flow. According to the one-dimensional through flow design program of the turbine, the one-dimensional through flow design of the power turbine under the full-load working condition is completed, and the one-dimensional through flow of the power turbine is obtained;
step three: the power distribution proportionality coefficient, the stage reaction degree and the relative front edge radius distribution rule of each row of blades of the given power turbine are provided. Setting a power distribution proportionality coefficient K of a first stage (a first stage) power and a final stage (a second stage) power of the power turbine according to a decreasing power distribution rule; giving the degree of reaction omega of the first stage (first stage) of the power turbine in the form of a decreasing degree of reaction distribution 1 And final (second) degree of reaction Ω 2 The method comprises the steps of carrying out a first treatment on the surface of the The relative front edge radius of each row of blades of the power turbine is given according to a constant relative front edge radius distribution form
Step four: power turbine IAnd (5) maintaining pneumatic design. Adopting a one-dimensional aerodynamic design program of a turbine to complete one-dimensional aerodynamic design of a power turbine under a full-load working condition, obtaining a one-dimensional aerodynamic calculation model of the turbine, judging whether the overall performance design index requirement of the marine gas turbine under the full-load working condition is met or not, if so, continuing to develop the subsequent steps, if not, repeating the steps two to four, and adjusting the power of a first stage (first stage) and the power distribution proportionality coefficient K of a last stage (second stage) according to a decreasing power distribution rule when the steps three, and adjusting the reaction degree omega of the first stage (first stage) of the power turbine according to a decreasing reaction degree 1 And final (second) degree of reaction Ω 2 Adjusting the relative leading edge radius of each row of blades of the power turbine according to the distribution form of the constant relative leading edge radius
Until the power turbine parameters meet the overall performance design index requirements of the whole machine under the full-load working condition;
step five: and (5) analyzing the aerodynamic performance of the power turbine under typical working conditions. Based on the one-dimensional aerodynamic calculation model of the power turbine, aiming at the unique working characteristics of constant-speed operation of the marine power generation type gas turbine, carrying out one-dimensional aerodynamic performance analysis of the power turbine under the typical working condition under the constant-speed condition to obtain one-dimensional aerodynamic results of the power turbine under the typical working condition, judging whether the overall performance of the whole machine meets the index requirement of the power turbine under the typical working condition, if the overall performance meets the requirement, continuing to carry out the subsequent steps, and if the overall performance of the whole machine does not meet the requirement, repeating the second to fifth steps until the parameters of the power turbine meet the overall performance index requirement of the whole machine under the typical working condition;
step six: and calculating the power turbine characteristics. Based on the one-dimensional aerodynamic calculation model of the power turbine obtained in the step four, carrying out power turbine characteristic calculation by adopting a one-dimensional aerodynamic calculation analysis program of the turbine to obtain turbine characteristic parameters such as turbine efficiency, flow and the like under the working state of different rotation speeds and expansion ratio arrangements and combinations;
step seven: and (5) overall performance evaluation of the whole machine under all working conditions. And D, carrying out complete machine full-working condition matching calculation of the marine power generation type gas turbine by utilizing the turbine characteristic parameters obtained in the step six, obtaining overall performance parameters such as complete machine full-working condition power, efficiency and the like of the marine power generation type gas turbine, evaluating whether the overall performance parameters meet the design index requirements under the full-working condition, if so, ending the design process, and if not, repeating the steps two to seven until the overall performance parameters meet the design index requirements under the full-working condition.
The "power turbine power distribution scaling factor" described in step three is defined as follows:
K=given value, K is more than or equal to 1.0 and less than or equal to 1.5.
The power turbine reaction degree omega described in the third step 1 、Ω 2 "is defined as follows:
Ω 1 Given value =0.35.ltoreq.Ω 1 ≤0.55。
Ω 2 Given value =0.25.ltoreq.Ω 2 ≤0.5。
Degree of reaction Ω of two-stage power turbine 1 、Ω 2 The relationship is as follows:
Ω 1 ≥Ω 2 。
the "relative leading edge radius of each row of blades" described in step three
The relationship "with the blade row number i" is defined as follows:
Claims (4)
1. A marine power generation type gas turbine double-stage high-speed power turbine pneumatic design method is characterized by comprising the following steps of:
(1) Determining power turbine design parameters: determining power turbine design parameters including power turbine inlet conditions, rotating speed, flow, expansion ratio, progression, first stage guide vane inlet size and last stage guide vane outlet size limit according to overall performance parameters of the marine gas turbine design working condition complete machine;
(2) And (3) designing a power turbine through flow: according to the one-dimensional through flow design program of the turbine, the one-dimensional through flow design of the power turbine under the full-load working condition is completed, and the one-dimensional through flow of the power turbine is obtained;
(3) Giving a power distribution proportionality coefficient, a stage reaction degree and a radius distribution rule of each row of blades relative to the front edge, and giving a first stage power and a last stage power distribution proportionality coefficient K of the power turbine according to a decreasing power distribution rule; the first-stage reaction degree omega of the power turbine is given according to the decreasing reaction degree distribution form 1 And final degree of reaction Ω 2 The method comprises the steps of carrying out a first treatment on the surface of the The relative front edge radius of each row of blades of the power turbine is given according to a constant relative front edge radius distribution form
(4) One-dimensional pneumatic design of a power turbine: adopting a one-dimensional aerodynamic design program of a turbine to complete one-dimensional aerodynamic design of a power turbine under a full-load working condition, obtaining a one-dimensional aerodynamic calculation model of the turbine, judging whether the overall performance design index requirement of the whole machine under the full-load working condition is met or not, if so, continuing to develop the subsequent steps, if not, repeating the steps (2) to (4), adjusting the first-stage power and the last-stage power distribution proportion coefficient K according to a decreasing power distribution rule when the step (3), and adjusting the first-stage reaction degree omega of the power turbine according to a decreasing reaction degree 1 And final degree of reaction Ω 2 Adjusting the relative leading edge radius of each row of blades of the power turbine according to the distribution form of the constant relative leading edge radius
Until the power turbine parameters meet the overall performance design index requirements of the whole machine under the full-load working condition;
(5) Analysis of aerodynamic performance of a power turbine under typical working conditions: based on the one-dimensional aerodynamic calculation model of the power turbine obtained in the step (4), aiming at the unique working characteristics of constant-speed operation of the marine power generation type gas turbine, carrying out one-dimensional aerodynamic performance analysis of the power turbine under the typical working condition under the constant-speed condition to obtain a one-dimensional aerodynamic result of the power turbine under the typical working condition, judging whether the overall performance of the whole machine meets the index requirement of the power turbine under the typical working condition, if the overall performance meets the requirement, continuing to carry out the subsequent steps, and if the overall performance of the whole machine does not meet the requirement, repeating the steps (2) to (5) until the parameters of the power turbine meet the overall performance index requirement of the whole machine under the typical working condition;
(6) Calculating the power turbine characteristics: based on the one-dimensional aerodynamic calculation model of the power turbine obtained in the step (4), carrying out power turbine characteristic calculation by adopting a one-dimensional aerodynamic calculation analysis program of the turbine to obtain turbine efficiency and flow turbine characteristic parameters under different rotation speeds and expansion ratio arrangement and combination working states;
(7) Overall performance evaluation of the whole machine under all working conditions: and (3) carrying out complete machine full-working condition matching calculation of the marine power generation type gas turbine by utilizing the turbine characteristic parameters obtained in the step (6), obtaining complete machine full-working condition power and efficiency overall performance parameters of the marine power generation type gas turbine, evaluating whether the overall performance parameters meet the design index requirements under the full-working condition, if so, ending the design process, and if not, repeating the steps (2) to (7) until the overall performance parameters meet the design index requirements under the full-working condition.
2. The method for pneumatically designing a two-stage high-speed power turbine of a marine power generation type gas turbine according to claim 1, wherein the method comprises the following steps of: the power turbine power split scaling factor described in step (3) is defined as follows:
k=given value, K is more than or equal to 1.0 and less than or equal to 1.5.
3. The method for pneumatically designing a two-stage high-speed power turbine of a marine power generation type gas turbine according to claim 1, wherein the method comprises the following steps of: degree of reaction Ω of the power turbine in step (3) 1 、Ω 2 The definition is as follows:
Ω 1 given value =0.35.ltoreq.Ω 1 ≤0.55；
Ω 2 Given value =0.25.ltoreq.Ω 2 ≤0.5；
Degree of reaction Ω of two-stage power turbine 1 、Ω 2 The relationship is as follows:
Ω 1 ≥Ω 2 。
4. the method for pneumatically designing a two-stage high-speed power turbine of a marine power generation type gas turbine according to claim 1, wherein the method comprises the following steps of: the relative leading edge radius of each row of blades in the step (3)
The relationship with the blade row number i is defined as follows:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210675151.1A CN115186440B (en) | 2022-06-15 | 2022-06-15 | Pneumatic design method for two-stage high-speed power turbine of marine power generation type gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210675151.1A CN115186440B (en) | 2022-06-15 | 2022-06-15 | Pneumatic design method for two-stage high-speed power turbine of marine power generation type gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115186440A CN115186440A (en) | 2022-10-14 |
| CN115186440B true CN115186440B (en) | 2023-06-27 |
Family
ID=83512984
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210675151.1A Active CN115186440B (en) | 2022-06-15 | 2022-06-15 | Pneumatic design method for two-stage high-speed power turbine of marine power generation type gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115186440B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108108528B (en) * | 2017-12-01 | 2021-05-25 | 中国科学院工程热物理研究所 | One-dimensional matching design method for power turbine of split-shaft type aeroderivative |
| CN109578085B (en) * | 2018-12-26 | 2021-06-22 | 中国船舶重工集团公司第七0三研究所 | Method for weakening unsteady acting force of turbine movable blade through guide blade inclination |
| US20210209264A1 (en) * | 2020-01-02 | 2021-07-08 | Viettel Group | Modeling and calculation aerodynamic performances of multi-stage transonic axial compressors |
| CN112528474B (en) * | 2020-11-30 | 2024-06-14 | 北京动力机械研究所 | One-dimensional pneumatic design method for guide vane-free counter-rotating turbine |
| CN113513373B (en) * | 2021-07-08 | 2023-05-30 | 哈尔滨工程大学 | One-dimensional pneumatic design method for variable geometry turbine |
| CN113607330A (en) * | 2021-07-26 | 2021-11-05 | 中国船舶重工集团公司第七0三研究所 | Method for measuring pressure of turbine chamber of marine gas turbine |
-
2022
- 2022-06-15 CN CN202210675151.1A patent/CN115186440B/en active Active
Non-Patent Citations (1)
| Title |
|---|
| 刘顺隆,冯永明,刘敏,王林.船用燃气轮机动力涡轮可调导叶级的流场结构.热能动力工程.2005,(02),13-17、105-106. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115186440A (en) | 2022-10-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112528575B (en) | Multi-dimensional collaborative design method for multistage axial flow compressor of ship gas turbine | |
| CN110929357A (en) | Pneumatic design method for high-performance ship gas turbine compressor | |
| CN109598081B (en) | Radial-flow turbine pneumatic optimization method based on data dimension reduction and multi-two-dimensional flow surface | |
| CN112685968B (en) | Axial flow compressor pneumatic design method based on space load customization thought | |
| US10352330B2 (en) | Turbomachine part with a non-axisymmetric surface | |
| CN112685851B (en) | Multi-stage axial flow compressor pneumatic design method based on key dimensionless load control parameters | |
| CN115017843A (en) | Pneumatic performance optimization design method for centrifugal compressor | |
| CN114444331A (en) | Stage characteristic matching method of multistage axial flow compressor | |
| CN113434965A (en) | Ship gas turbine compressor performance optimization method based on three-dimensional flow field analysis | |
| CN115186440B (en) | Pneumatic design method for two-stage high-speed power turbine of marine power generation type gas turbine | |
| CN112699503B (en) | Method for designing inverse problem of S2 of axial flow compressor based on dimensionless load control parameters | |
| CN110245408B (en) | Design method for single-arc pressure surface blade profile of steam turbine | |
| CN115186443B (en) | Pneumatic design method for multistage power turbine of power generation type gas turbine for inverted bathtub load ship | |
| CN112685852A (en) | Axial flow compressor load customized pneumatic optimization method capable of keeping continuity of through-flow structure | |
| CN115186442B (en) | Multi-stage power turbine pneumatic design method for power generation type gas turbine for decreasing load ship | |
| CN115186441B (en) | Pneumatic design method for multistage power turbine of power generation type gas turbine for incremental load ship | |
| CN115221650A (en) | Axial flow turbine three-dimensional blade design method based on radial speed ratio optimization | |
| Nagel et al. | Experimentally verified numerical optimisation of a 3d-parametrized turbine vane with non-axisymmetric end walls | |
| CN114756954A (en) | Through-flow load one-dimensional design method for wide-margin low-pressure compressor of three-rotor marine gas turbine | |
| CN115114750B (en) | Multi-working-point optimization method for wide-working-condition power turbine | |
| CN115270318B (en) | Transonic moving blade modeling method for axial-flow compressor of marine gas turbine | |
| CN113137282B (en) | Reaction turbine stage group connection structure and structural parameter design method thereof | |
| Chen et al. | Research on optimization of the design (inverse) issue of S2 surface of axial compressor based on genetic algorithm | |
| CN115455608A (en) | Novel gas turbine axial flow compressor blade profile optimization method | |
| CN111382539B (en) | Turbomachine blade profile optimization method based on through-flow calculation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |