A reaction-type turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine

Abstract

This invention discloses a reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine, relating to the field of liquid rocket engine technology, including the following steps: (1) obtaining aerodynamic design input parameters; (2) calculating the total isentropic expansion specific work and estimating aerodynamic efficiency; (3) selecting the number of turbine stages and determining the isentropic enthalpy drop ratio and thermodynamic reaction degree of each stage; (4) selecting the speed ratio of each stage and calculating the turbine mean diameter and specific speed; (5) calculating the aerodynamic and geometric parameters of the blade cascade; (6) drawing the cross-sectional profiles of the moving and stationary blade cascades of each stage and stacking them to form a three-dimensional blade cascade profile; (7) three-dimensional modeling of the flow path model; (8) three-dimensional aerodynamic simulation and performance analysis; (9) determining whether the aerodynamic performance meets the requirements. The reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine of this invention can reduce the development risk of a full-flow staged combustion liquid rocket engine and has a wide range of applications in the field of rocket engines.

Description

Technical Field

[0001] This invention relates to the field of liquid rocket engine technology, and in particular to a reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine. Background Technology

[0002] Full-flow staged combustion liquid rocket engines are the core propulsion solution for future heavy-lift space launch vehicles and reusable space rockets. Because almost all propellant undergoes combustion in the pre-combustion chamber, work in the gas turbine, and final exhaust into the thrust chamber for afterburning, the chemical energy of the propellant is converted into the kinetic energy of the rocket engine to the greatest extent possible. Full-flow staged combustion liquid rocket engines possess advantages such as high temperature, high pressure, high speed, and high specific impulse. The reaction turbine is the core component of a full-flow staged combustion liquid rocket engine, and its design methodology differs significantly from that of the impulse turbine in open-cycle liquid rocket engines. Currently, there is a lack of a clear, comprehensive, and well-defined design methodology for reaction turbines, posing considerable difficulties and challenges to the development of full-flow staged combustion liquid rocket engines. Summary of the Invention

[0003] The purpose of this invention is to overcome the shortcomings of the prior art and provide an aerodynamic design method for a reaction turbine of a full-flow staged combustion liquid rocket engine, further clarifying the aerodynamic design process of the reaction turbine of a full-flow staged combustion liquid rocket engine.

[0004] The technical solution adopted by this invention to solve its technical problem is as follows:

[0005] A reaction-force turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine includes the following steps:

[0006] (1) Obtain the aerodynamic design input parameters for the reaction turbine;

[0007] (2) Calculate the total isentropic expansion specific work of the reaction turbine, estimate the aerodynamic efficiency of the reaction turbine, and back-calculate the gas flow rate;

[0008] (3) Select the number of reaction turbine stages and determine the isentropic enthalpy drop ratio and thermal reaction degree of each stage;

[0009] (4) Based on the design level of the reaction turbine, select the speed ratio of each stage and calculate the turbine mean diameter and specific speed;

[0010] (5) Calculate the inlet and outlet aerodynamic and geometric parameters of each stage of the moving and stationary blade cascades;

[0011] (6) Based on the aerodynamic characteristics of the blade cascade, draw the cross-sectional profiles of each stage of the moving and stationary blade cascades along the blade height direction, and stack the profiles to form the three-dimensional profile of the blade cascade;

[0012] (7) Three-dimensional modeling of the flow path of the reaction turbine intake passage, dynamic and static blade passage, and exhaust passage;

[0013] (8) Three-dimensional simulation and performance analysis of reaction turbine aerodynamics;

[0014] (9) Determine whether the aerodynamic performance meets the requirements. If not, return to step 3 to redesign; if it does, the design is complete.

[0015] Preferably, the reaction turbine has two stages, which can reduce the radial dimension of the reaction turbine and improve aerodynamic efficiency without increasing the structural complexity of the reaction turbine.

[0016] Preferably, the thermal reaction degree is 0.1~0.3, which can reduce the axial force of the reaction turbine while ensuring the high aerodynamic efficiency of the reaction turbine.

[0017] Preferably, the speed ratio of each stage is 0.35 to 0.7, which can improve aerodynamic efficiency while ensuring the compact radial dimensions of the reaction turbine.

[0018] Preferably, the inlet and outlet aerodynamic parameters of the moving and stationary blade cascades at each stage include temperature, pressure, density, velocity, and airflow angle at the inlet and outlet of the blade cascades, and the inlet and outlet geometric parameters of the moving and stationary blade cascades at each stage include blade height and blade installation angle at the inlet and outlet of the blade cascades.

[0019] Preferably, when calculating the inlet and outlet aerodynamic and geometric parameters of each stage of the moving and stationary blade cascade, the aerodynamic function calculation method of the actual expansion of an ideal gas is adopted.

[0020] Preferably, when drawing the cross-sectional profiles of the moving and stationary blades at each level along the blade height direction, the blade profiles are bent, twisted, and swept to adapt to the airflow characteristics in the blade channel.

[0021] Preferably, when modeling the flow path of the reaction turbine inlet channel, the moving and stationary blade channel, and the exhaust channel in three dimensions, the flow characteristics of the airflow in the blade channel are combined to create a non-axisymmetric endwall shape for the turbine blade channel endwall, so as to reduce the aerodynamic loss of the airflow in the blade endwall region.

[0022] Compared with the prior art, the present invention has the following advantages:

[0023] (1) This invention proposes a complete reaction turbine aerodynamic design method for full-flow staged combustion liquid rocket engines. Based on the aerodynamic design method, the reaction turbine aerodynamic optimization design of full-flow staged combustion liquid rocket engines can be realized, thereby reducing the cost and risk of forward development of full-flow staged combustion liquid rocket engines. Attached Figure Description

[0024] To more clearly illustrate the technical solutions of the embodiments of this invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0025] Figure 1 As an example, this invention provides a reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine. Detailed Implementation

[0026] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0028] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0029] Example

[0030] See Figure 1 The diagram shows a reaction-type turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine. Figure 1 As shown, the method includes the following steps S1-S10.

[0031] S1, obtain the input parameters for the reaction turbine aerodynamic design.

[0032] S2 calculates the total isentropic expansion specific work of the reaction turbine, estimates the aerodynamic efficiency of the reaction turbine, and calculates the gas flow rate.

[0033] S3, select the number of reaction turbine stages, and determine the isentropic enthalpy drop ratio and thermodynamic reaction degree of each stage.

[0034] In one embodiment, the reaction turbine is selected to have 2 stages. Without increasing the structural complexity of the reaction turbine, the radial dimension of the reaction turbine can be reduced and the aerodynamic efficiency can be improved.

[0035] In one embodiment, a thermal reaction degree of 0.1 to 0.3 is selected, which can reduce the axial force of the reaction turbine while ensuring the high aerodynamic efficiency of the reaction turbine.

[0036] S4, based on the design level of the reaction turbine, select the speed ratio of each stage, and calculate the turbine mean diameter and specific speed.

[0037] In one embodiment, the speed ratio of each stage is selected to be 0.35~0.7, which can improve aerodynamic efficiency while ensuring the compact radial dimensions of the reaction turbine.

[0038] S5 calculates the inlet and outlet aerodynamic and geometric parameters of each stage of the moving and stationary blade cascades.

[0039] In one embodiment, the inlet and outlet aerodynamic parameters of each stage of the moving and stationary blade cascades include temperature, pressure, density, velocity, and airflow angle at the inlet and outlet of the blade cascades, and the inlet and outlet geometric parameters of each stage of the moving and stationary blade cascades include blade height and blade installation angle at the inlet and outlet of the blade cascades.

[0040] In one embodiment, the aerodynamic and geometric parameters of the inlet and outlet of each stage of the moving and stationary blade cascade are calculated using the aerodynamic function calculation method of the actual expansion of an ideal gas.

[0041] S6. Based on the aerodynamic characteristics of the blade cascade, draw the cross-sectional profiles of each stage of the moving and stationary blade cascades along the blade height direction, and stack the profiles to form the three-dimensional profile of the blade cascade.

[0042] In one embodiment, when drawing the cross-sectional profiles of each level of moving and stationary blades along the blade height direction, the blade profile is bent, twisted, and swept to adapt to the airflow, taking into account the flow characteristics of the airflow in the blade channel.

[0043] S7, 3D modeling of the flow path of the reaction turbine intake passage, moving and stationary blade passage, and exhaust passage.

[0044] In one embodiment, when the flow path model of the reaction turbine inlet passage, the moving and stationary blade passage, and the exhaust passage is modeled in three dimensions, the flow characteristics of the airflow in the blade passage are combined to create a non-axisymmetric endwall shape for the turbine blade passage endwall, so as to reduce the aerodynamic loss of the airflow in the blade passage endwall region.

[0045] S8, 3D simulation and performance analysis of reaction turbine aerodynamics.

[0046] S9. Determine if the aerodynamic performance meets the requirements. If not, return to step S3 to redesign.

[0047] If S10 is satisfied, the design is complete.

[0048] The reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine of the present invention can realize the optimized design of the reaction turbine aerodynamics of a full-flow staged combustion liquid rocket engine, thereby reducing the cost and risk of forward development of a full-flow staged combustion liquid rocket engine, and has a wide range of applications in the field of rocket engines.

[0049] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should all be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

[0050] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A reaction-type turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine, characterized in that, Includes the following steps: (1) Obtain the aerodynamic design input parameters for the reaction turbine; (2) Calculate the total isentropic expansion specific work of the reaction turbine, estimate the aerodynamic efficiency of the reaction turbine, and back-calculate the gas flow rate; (3) Select the number of reaction turbine stages and determine the isentropic enthalpy drop ratio and thermal reaction degree of each stage; (4) Based on the design level of the reaction turbine, select the speed ratio of each stage and calculate the turbine mean diameter and specific speed; (5) Calculate the inlet and outlet aerodynamic and geometric parameters of each stage of the moving and stationary blade cascades; (6) Based on the aerodynamic characteristics of the blade cascade, draw the cross-sectional profiles of each stage of the moving and stationary blade cascades along the blade height direction, and stack the profiles to form the three-dimensional profile of the blade cascade; (7) Three-dimensional modeling of the flow path of the reaction turbine intake passage, dynamic and static blade passage, and exhaust passage; (8) Three-dimensional simulation and performance analysis of reaction turbine aerodynamics; (9) Determine whether the aerodynamic performance meets the requirements. If not, return to step 3 to redesign; if it does, the design is complete.

2. The reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that, The reaction turbine has two stages, which can reduce the radial dimension and improve aerodynamic efficiency without increasing the structural complexity of the reaction turbine.

3. The reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that, The aforementioned thermal reaction degree is 0.1~0.3, which can reduce the axial force of the reaction turbine while ensuring high aerodynamic efficiency.

4. The reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that, The speed ratios of each stage are 0.35 to 0.7, which can improve aerodynamic efficiency while ensuring the compact radial dimensions of the reaction turbine.

5. The reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that, The inlet and outlet aerodynamic parameters of each stage of the moving and stationary blade cascades include temperature, pressure, density, velocity, and airflow angle at the inlet and outlet of the blade cascades. The inlet and outlet geometric parameters of each stage of the moving and stationary blade cascades include blade height and blade installation angle at the inlet and outlet of the blade cascades.

6. The reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that, The calculation of the inlet and outlet aerodynamic and geometric parameters of each stage of the moving and stationary blade cascades adopts the aerodynamic function calculation method of the actual expansion of an ideal gas.

7. The reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that, When drawing the cross-sectional profiles of the moving and stationary blades at each level along the blade height direction, the blade profiles are bent, twisted, and swept to adapt to the airflow characteristics in the blade channel.

8. The reaction turbine aerodynamic design method for a full-flow staged combustion liquid rocket engine according to claim 1, characterized in that, When modeling the flow path of the reaction turbine inlet channel, the moving and stationary blade channel, and the exhaust channel in three dimensions, the flow characteristics of the airflow in the blade channel are combined to create a non-axisymmetric endwall shape for the turbine blade channel endwall, so as to reduce the aerodynamic loss of the airflow in the blade endwall region.

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