CN115163330A - Method for determining stable boundary of compression system of double-duct core machine - Google Patents
Method for determining stable boundary of compression system of double-duct core machine Download PDFInfo
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- CN115163330A CN115163330A CN202210626268.0A CN202210626268A CN115163330A CN 115163330 A CN115163330 A CN 115163330A CN 202210626268 A CN202210626268 A CN 202210626268A CN 115163330 A CN115163330 A CN 115163330A
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- 230000001052 transient effect Effects 0.000 claims description 9
- 230000003068 static effect Effects 0.000 claims description 7
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
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- 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
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- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a method for determining a stable boundary of a compression system of a double-duct core machine, and belongs to the technical field of turbofan engines. The method comprises the steps of measuring and calculating the stable boundary of a compressor and a core engine driving fan (CDFS) under the test state of the engine core engine. The method can be used for analyzing the surge boundary of the CDFS and the compressor in a turbofan engine and double-culvert core engine surge test.
Description
Technical Field
The invention belongs to the technical field of turbofan engines, and particularly relates to a method for determining a stable boundary of a compression system of a double-duct core machine.
Background
With the development of engine research and tests, when the air compressor is installed on an engine, the characteristic line is obviously different from the characteristic line obtained on a test bed of an air compressor component, particularly the stability boundary of the air compressor, and in the past research work, an isolated compression component is taken as a research object, and both numerical calculation and test are carried out by taking the air compressor component as an upper outlet exhaust cavity and an outlet exhaust cavity as the research object, so that the stability margin under the installation state of the engine cannot be accurately determined, and the accuracy of aerodynamic stability evaluation is influenced.
The inlet flow of a compressor in the double-duct core machine can not be directly measured and calculated generally, and the steady-state flow is obtained by 2 methods: and performing iterative calculation according to the temperature behind the turbine and the critical reduced flow of the turbine. And the flow of the transient operating point and the stable boundary point cannot be obtained through iterative calculation.
The stable boundary of the compression system in the core machine state is generally obtained by adopting a surge-type test. In the surge-inducing test, the calculation and measurement of the transient working point, particularly the stable boundary point of the compression system can only determine the total flow and the pressure ratio of a core engine driving fan (CDFS) and the compressor through an inlet flow pipe and pressure probes of various characteristic sections to determine the stable boundary, and the flow of the stable boundary of the compressor cannot be obtained.
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide a method for obtaining stable boundary points of a CDFS and a compressor in a core engine state, so as to determine an accurate stability margin of a compression system in an installed state.
In order to achieve the above object, the present invention provides a method for determining a stable boundary of a compression system of a dual-ducted core engine, the method using a transient loading surge-approaching test of an aircraft gas turbine engine, the method comprising the following steps:
s1: acquiring the air inlet flow at the instability moment of a core machine and the total pressure ratio of stable boundary points of a compression system of the core machine, wherein the compression system of the core machine comprises a core machine driving fan and a gas compressor;
s2: obtaining the inlet flow of the core machine driving fan according to the inlet flow of the core machine at the instability moment obtained in the S1, and calculating the stable boundary pressure ratio of the core machine driving fan at the instability moment;
s3: measuring the total pressure of the outlet of the core machine driving fan and the dynamic total pressure of the outlet of the compressor, calculating to obtain the pressure ratio of the instability moment of the compressor, and interpolating according to the pressure ratio and the rotating speed of the compressor and the test characteristics of isolated compressor components to obtain the inlet flow of the compressor at the instability moment;
s4: and determining the stable boundary of the compression system of the core machine according to the air inlet flow at the instability moment of the core machine, the total pressure ratio of the stable boundary points of the compression system of the core machine, the inlet flow of the driving fan of the core machine, the stable boundary pressure ratio of the driving fan of the core machine at the instability moment, the pressure ratio at the instability moment of the compressor and the inlet flow of the compressor at the instability moment.
The method for determining the stable boundary of the compression system of the double-duct core machine is further characterized in that the air inlet flow at the instability moment of the core machine in the S1 is obtained by calculating the total pressure, the static pressure and the total temperature of the flow tube.
The method for determining the stable boundary of the compression system of the double-duct core machine, provided by the invention, has the characteristics that the total pressure ratio of the stable boundary point of the compression system of the core machine in the S1 is calculated through the dynamic total pressure of the inlet of the core machine driving fan and the dynamic total pressure of the outlet of the compressor.
The method for determining the stable boundary of the compression system of the double-duct core machine is further characterized in that the inlet flow of the core machine driving fan in the S2 is equal to the inlet flow of the core machine at the instability moment.
The method for determining the stable boundary of the compression system of the double-duct core machine provided by the invention has the characteristics that if the dynamic total pressure of the outlet of the core machine driving fan can be measured, the stable boundary pressure ratio of the core machine driving fan is calculated through the dynamic total pressure of the inlet and the dynamic total pressure of the outlet of the core machine driving fan.
The method for determining the stable boundary of the compression system of the double-duct core machine, provided by the invention, has the characteristics that if the dynamic total pressure of the outlet of the core machine driving fan cannot be measured, the total pressure of the outlet of the core machine driving fan at the instability moment is obtained by adopting a method of correlating the dynamic static pressure with the steady state total pressure of the outer wall, and the stable boundary pressure ratio of the core machine driving fan is calculated through the total pressure of the outlet of the core machine fan and the dynamic total pressure of the inlet of the core machine driving fan.
Advantageous effects
The method for determining the stable boundary of the compression system of the double-duct core machine can be used for measuring and calculating the stable boundary points of the total characteristics of the compression system and the characteristics of the core machine driving fan and the air compressor during transient loading surge-approaching test.
Drawings
FIG. 1 is a diagram illustrating a dynamic static pressure of an outer wall of a CDFS outlet as a function of a steady pressure and a total pressure of the CDFS outlet in an embodiment of the present invention;
FIG. 2 is a steady state boundary and compression system component test derived features of the compression system under transient loading test in the overall environment of the present invention;
FIG. 3 is a steady state boundary obtained by a transient loading test of a core machine driven fan in a complete machine environment and features obtained by a test of an isolated core machine driven fan component in an embodiment of the present invention;
fig. 4 shows steady-state boundaries obtained by transient loading tests of the compressor in the whole environment and features obtained by tests of isolated compressor components in the embodiment of the invention.
Detailed Description
The present invention is further described in detail with reference to the drawings and examples, but it should be understood that these embodiments are not intended to limit the present invention, and those skilled in the art should understand that the functional, methodological, or structural equivalents of these embodiments or substitutions may be included in the scope of the present invention.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, "a plurality" means two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
1-4, the present embodiment provides a method for determining a stability boundary of a dual-ducted core compressor system using a transient loading surge-like test in an aircraft gas turbine engine, the method comprising the steps of:
s1: acquiring the air inlet flow at the instability moment of a core machine and the total pressure ratio of stable boundary points of a compression system of the core machine, wherein the compression system of the core machine comprises a core machine driving fan and a gas compressor;
s2: obtaining the inlet flow of the core machine driving fan according to the inlet flow of the core machine at the instability moment of the core machine obtained in the step S1, and calculating the stable boundary pressure ratio of the core machine driving fan at the instability moment;
s3: measuring the total pressure of the outlet of the core machine driving fan and the dynamic total pressure of the outlet of the compressor, calculating to obtain the pressure ratio of the instability moment of the compressor, and interpolating according to the pressure ratio and the rotating speed of the compressor and the test characteristics of isolated compressor components to obtain the inlet flow of the compressor at the instability moment;
s4: and determining the stable boundary of the compression system of the core machine according to the air inlet flow at the instability moment of the core machine, the total pressure ratio of the stable boundary points of the compression system of the core machine, the inlet flow of the driving fan of the core machine, the stable boundary pressure ratio of the driving fan of the core machine at the instability moment, the pressure ratio at the instability moment of the compressor and the inlet flow of the compressor at the instability moment.
As shown in fig. 2 to 4, a stable boundary of the compression system in the core machine state, a stable boundary of the core machine driving fan in the core machine state, and a stable boundary of the compressor in the core machine state are obtained, respectively.
In some embodiments, the intake air flow rate at the time of instability of the core engine in S1 is obtained by calculating the total pressure, the static pressure and the total temperature of the flow tube.
In some embodiments, the total pressure ratio of the stable boundary point of the core compressor system in S1 is calculated by the core compressor driving fan inlet dynamic total pressure and the compressor outlet dynamic total pressure.
In some embodiments, the core engine driven fan inlet flow rate in S2 is equal to the core engine unsteady time inlet flow rate.
In some embodiments, if the dynamic total pressure at the core driver fan outlet can be measured, the core driver fan stable boundary pressure ratio is calculated from the core driver fan inlet dynamic and outlet dynamic total pressures.
In some embodiments, if the dynamic total pressure at the outlet of the core machine driving fan cannot be measured, the total pressure at the outlet of the core machine driving fan at the moment of instability is obtained by using an outer wall dynamic static pressure correlation steady state total pressure method, and then the stable boundary pressure ratio of the core machine driving fan is calculated through the total pressure at the outlet of the core machine fan and the dynamic total pressure at the inlet of the core machine driving fan.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (6)
1. A method for determining a stability boundary of a compression system of a dual-bypass core engine, the method using a transient loading surge-like test of an aircraft gas turbine engine, the method comprising the steps of:
s1: acquiring the air inlet flow at the instability moment of a core machine and the total pressure ratio of stable boundary points of a compression system of the core machine, wherein the compression system of the core machine comprises a core machine driving fan and a gas compressor;
s2: obtaining the inlet flow of the core machine driving fan according to the inlet flow of the core machine at the instability moment obtained in the S1, and calculating the stable boundary pressure ratio of the core machine driving fan at the instability moment;
s3: measuring the total pressure of an outlet of a driving fan of the core machine and the dynamic total pressure of an outlet of the gas compressor, calculating to obtain the pressure ratio of the instability moment of the gas compressor, and interpolating according to the pressure ratio and the rotating speed of the gas compressor and the test characteristics of an isolated gas compressor part to obtain the inlet flow of the gas compressor at the instability moment;
s4: and determining the stable boundary of the compression system of the core machine according to the air inlet flow at the instability moment of the core machine, the total pressure ratio of the stable boundary points of the compression system of the core machine, the inlet flow of the driving fan of the core machine, the stable boundary pressure ratio of the driving fan of the core machine at the instability moment, the pressure ratio at the instability moment of the compressor and the inlet flow of the compressor at the instability moment.
2. The method for determining the stable boundary of the compression system of the double-duct core engine according to claim 1, wherein the intake air flow rate at the time of the core engine instability in S1 is obtained by calculating the total pressure, the static pressure and the total temperature of the flow tube.
3. The method for determining the stable boundary of the dual-duct core compressor system according to claim 1, wherein the total pressure ratio of the stable boundary point of the core compressor system in the S1 is calculated by the core-driven fan inlet dynamic total pressure and the compressor outlet dynamic total pressure.
4. The method of claim 1, wherein the core-driven fan inlet flow rate in S2 is equal to the core intake air flow rate at the moment of core instability.
5. The method of claim 1, wherein if the dynamic total pressures at the outlet of the core driven fan can be measured, the core driven fan stable boundary pressure ratio is calculated from the core driven fan inlet dynamic and outlet dynamic total pressures.
6. The method for determining the stable boundary of the compression system of the double-duct core machine according to claim 1, wherein if the dynamic total pressure at the outlet of the core machine driving fan cannot be measured, the total pressure at the outlet of the core machine driving fan at the instability moment is obtained by using a method of associating the dynamic static pressure with the steady state total pressure on the outer wall, and then the stable boundary pressure ratio of the core machine driving fan is calculated through the total pressure at the outlet of the core machine fan and the dynamic total pressure at the inlet of the core machine driving fan.
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