CN106251068B - A kind of total state bird based on fan part bird impact tests result hits appraisal procedure - Google Patents

A kind of total state bird based on fan part bird impact tests result hits appraisal procedure Download PDF

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CN106251068B
CN106251068B CN201610616726.7A CN201610616726A CN106251068B CN 106251068 B CN106251068 B CN 106251068B CN 201610616726 A CN201610616726 A CN 201610616726A CN 106251068 B CN106251068 B CN 106251068B
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bird
angular momentum
blade
fan
damage
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CN106251068A (en
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赵肃
施磊
任智博
谢业平
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AVIC Shenyang Engine Design and Research Institute
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Abstract

The invention discloses a kind of total state birds based on fan part bird impact tests result to hit appraisal procedure.Described method includes following steps: step 1: obtaining birds variable parameter, fan part variable parameter；Step 2: being formed in the combinatorial matrix that the parameter of selection is combined with each other, a combination parameter in each combinatorial matrix is one group of parameter state；Step 3: calculate under each group of parameter state with respect to the bending failure angular momentum of blade root and relative vane center of rotation torque failure angular momentum；Step 4: the torque failure angular momentum of the center of rotation of the bending failure angular momentum of opposite blade root corresponding to every group of parameter state and relative vane is compared with limiting safe angular momentum and limiting damage angular momentum respectively.Total state bird based on fan part bird impact tests result of the invention hits the total state bird that appraisal procedure proposes completely based on component bird impact tests result and hits appraisal procedure.

Description

Full-state bird strike evaluation method based on bird strike test result of fan component
Technical Field
The invention relates to the technical field of bird strike tests, in particular to a full-state bird strike evaluation method based on a bird strike test result of a fan component.
Background
The bird strike test of the fan component of the existing aircraft engine is mainly carried out under the conditions of different fan rotating speeds, bird weights, bird speeds and the like, and the bird strike test of the component cannot comprehensively evaluate all state points in a flight envelope of the aircraft engine and the strike conditions of various bird bodies due to the fact that the adjustable parameters are more and are limited by test resources.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a full-state bird strike assessment method based on fan assembly bird strike test results that overcomes or at least alleviates at least one of the above-mentioned deficiencies in the prior art.
In order to achieve the above object, the present invention provides a full-state bird strike evaluation method based on a fan component bird strike test result, wherein the full-state bird strike evaluation method based on the fan component bird strike test result comprises the following steps: step 1: acquiring bird variable parameters and fan component variable parameters; step 2: selecting a plurality of parameters in the bird variable parameters and the fan component variable parameters in the step 1, and forming a combined matrix in which the selected parameters are combined with each other, wherein one combined parameter in each combined matrix is a group of parameter states; and step 3: calculating a bending damage angular momentum of the bird body relative to the blade root when the bird body acts on the fan component and a twisting damage angular momentum of the bird body relative to the rotation center of the blade when the bird body acts on the fan component under the parameter state of each group in the step 2 through a formula; and 4, step 4: comparing the bending damage angular momentum of the blade root and the torsion damage angular momentum of the rotation center of the blade, which are obtained in the step 3 and correspond to each group of parameter states in the step 2, with the limit safety angular momentum and the limit damage angular momentum respectively, so as to obtain the states of the fan component in the group of parameter states.
Preferably, the bird variable parameters in step 1 include: bird body weight, bird body area, bird body density, bird body speed.
Preferably, the fan component parameters are the rotating speed of the blades in the fan component, the blade radius of the blades in the fan component and the number of the blades in the fan component.
Preferably, the bird variable parameters and fan component variable parameters selected in step 2 in step 1 include: fan speed parameter, bird body weight parameter, bird body speed parameter in the fan subassembly.
Preferably, the bending failure angular momentum formula of the opposite blade root in the step 2 is as follows:wherein M isBBird mass for each blade;is the velocity of failure perpendicular to the blade chord line at impact height; h is the impact height of the bird on the blade.
Preferably, said V is calculated using the following formula:wherein i is the inclination angle of the blade, α'2Is the blade exit angle;
the M isBCalculated using the following formula:
wherein,u is blade speed, VAAxial speed of the bird entering the engine, aBProjected area of bird at engine inlet, ρBBird density.
Preferably, the torsional damage angular momentum relative to the rotation center of the blade in step 2 is calculated by using the following formula:
wherein, VrelFor the resultant speed of the bird entering the engine, z is the length along the chord from the inlet edge to the center of rotation, L is the length of the bird chopped up by one rotor blade, θ is the angle of incidence of the bird's body with respect to the chord, θ' is the chord angle, ρBIs bird body density, ABIs the cross-sectional area of the bird hitting the blade.
Preferably, the ultimate safe angular momentum and the ultimate destruction angular momentum in the step 4 are obtained through experiments.
Preferably, the state of the fan part includes the following states: when the bending damage angular momentum relative to the blade root is smaller than the ultimate safe angular momentum, the fan part is in the damage standard range; when the torsional damage angular momentum relative to the center of rotation of the blade is less than the ultimate safe angular momentum, the fan component is within the damage standard range; when the bending damage angular momentum relative to the blade root is larger than the ultimate damage angular momentum, the fan component exceeds the damage standard range; when the torsional failure angular momentum relative to the rotational center of the blade is greater than the ultimate failure angular momentum, the fan component will exceed the damage criteria range.
In the full-state bird impact evaluation method based on the bird impact test result of the fan component, the complete full-state bird impact evaluation method based on the bird impact test result of the component is provided, and the bird impact capability of the fan component in the full-speed, full-bird weight and full-bird speed states can be quickly and accurately evaluated by using the limited test result.
Drawings
Fig. 1 is a force diagram illustrating bending failure angular momentum of a fan unit relative to a blade root in a full-state bird strike evaluation method based on bird strike test results of the fan unit according to an embodiment of the present invention.
Fig. 2 is a vector diagram illustrating bending failure angular momentum of the fan unit with respect to the blade root in the full-state bird strike evaluation method based on bird strike test results of the fan unit shown in fig. 1.
Fig. 3 is a force diagram illustrating a torsional damage angular momentum generated by a fan unit with respect to a rotational center of a blade in a full-state bird strike evaluation method based on bird strike test results of the fan unit according to an embodiment of the present invention.
Reference numerals:
1. a blade;
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "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 used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
Fig. 1 is a force diagram illustrating bending failure angular momentum of a fan unit relative to a blade root in a full-state bird strike evaluation method based on bird strike test results of the fan unit according to an embodiment of the present invention.
Fig. 2 is a vector diagram illustrating bending failure angular momentum of the fan unit with respect to the blade root in the full-state bird strike evaluation method based on bird strike test results of the fan unit shown in fig. 1.
Fig. 3 is a force diagram illustrating a torsional damage angular momentum generated by a fan unit with respect to a rotational center of a blade in a full-state bird strike evaluation method based on bird strike test results of the fan unit according to an embodiment of the present invention.
The full-state bird strike evaluation method based on the fan assembly bird strike test results shown in fig. 1 to 3 includes the steps of: step 1: acquiring bird variable parameters and fan component variable parameters; step 2: selecting a plurality of parameters in the bird variable parameters and the fan component variable parameters in the step 1, and forming a combination matrix formed by mutually combining the selected parameters, wherein one combination parameter in each combination matrix is a group of parameter states; and step 3: calculating a bending damage angular momentum of the bird body relative to the blade root when the bird body acts on the fan component and a twisting damage angular momentum of the bird body relative to the rotation center of the blade when the bird body acts on the fan component under the parameter state of each group in the step 2 through a formula; and 4, step 4: comparing the bending damage angular momentum of the blade root and the torsion damage angular momentum of the rotation center of the blade, which are obtained in the step 3 and correspond to each group of parameter states in the step 2, with the limit safety angular momentum and the limit damage angular momentum respectively, so as to obtain the states of the fan component in the group of parameter states.
In this example, bird variable parameters in step 1 include: bird body weight, bird body area, bird body density, bird body speed.
In the present embodiment, the fan component parameters are the rotational speed of the blades in the fan component, the blade radius of the blades in the fan component, and the number of blades of the blades in the fan component.
In this embodiment, the bird variable parameters and fan component variable parameters selected in step 1 in step 2 include: fan speed parameter, bird body weight parameter, bird body speed parameter in the fan subassembly.
Referring to fig. 1 to 2, in the present embodiment, the bending failure angular momentum of the opposite blade root in step 2 is expressed as:wherein M isBBird mass for each blade;is the velocity of failure perpendicular to the blade chord line at impact height; h is the impact height of the bird on the blade.
In the aboveCalculated using the following formula:wherein i is the inclination angle of the blade (i shown in FIGS. 1 and 2), α'2Is the blade exit angle (α 'shown in FIGS. 2 and 1)'2)；
The M isBCalculated using the following formula:
wherein,u isBlade speed, VAAxial speed of the bird into the engine, ABIs the projected area of the bird at the engine inlet, pBIs the density of birds.
In the present embodiment, the torsional breaking angular momentum with respect to the rotation center of the blade in step 2 is calculated using the following equation:
wherein, VrelThe resultant speed at which the bird enters the engine, z being the length along the chord of the blade from the inlet edge to the center of rotation, L being the length of the bird chopped up by one rotor blade; theta' is the angle shown in fig. 3. RhoBIs the density of birds. A. theBIs the projected area of the bird at the engine inlet.
In this embodiment, the ultimate safe angular momentum and the ultimate destruction angular momentum in step 4 are obtained through experiments. Specifically, the ultimate failure state and the ultimate safety state may be determined based on the existing bird strike test results of the fan components according to the blade damage criteria specified for the corresponding engine, according to the formula:and finishing the calculation of the ultimate safe angular momentum and the ultimate destruction angular momentum.
In the present embodiment, the states of the fan section include the following states:
when the bending damage angular momentum relative to the blade root is smaller than the ultimate safe angular momentum, the fan part is in the damage standard range;
when the torsional damage angular momentum relative to the center of rotation of the blade is less than the ultimate safe angular momentum, the fan component is within the damage standard range;
when the bending damage angular momentum relative to the blade root is larger than the ultimate damage angular momentum, the fan component exceeds the damage standard range;
when the torsional failure angular momentum relative to the rotational center of the blade is greater than the ultimate failure angular momentum, the fan component will exceed the damage criteria range.
The invention is further illustrated by way of example below. It will be understood that this example does not constitute any limitation of the invention.
Example (b):
performing bird collision test of fan parts, obtaining bird variable parameters and fan part variable parameters, and calculating bending damage angular momentum M of blade root according to the above formulaAAnd torsional breaking angular momentum M relative to the center of rotation of the bladeθ。
According to MAAnd MθThe numerical values are sorted from small to large, and the fan rotating speed parameter, the bird body weight parameter and the bird body speed parameter in the corresponding fan assembly are changed accordingly.
As exemplified in the following table,
the calculated variables are fan speed, bird weight, bird speed. And combining the state points according to the possible rotating speed range, the bird weight range and the bird speed range.
Such as: the fan rotating speed range is 500-8000 r/min, and 16 rotating speed states are formed in every 500 rotating speeds at one point
The weight range of the bird body is 50-3000 g, and 60 bird body states are formed at every 50g point
The bird speed range is 50-200 m/s, and 31 speed states are formed at every 5m/s
After combination, a total of 16 × 60 × 31 ═ 29760 state points
Respectively calculating M of all state points according to a formulaAAnd Mθ。
When M isA≤MAsWhen the bending failure is within the damage standard range;
when M isθ≤MθsWhen the damage is within the damage standard range, the torsion damage is within the damage standard range;
when M isA≥MApWhen the bending damage exceeds the damage standard range;
when M isθ≥MθpAt times, torsional failure will exceed the damage criteria.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims (8)

1. A full-state bird strike evaluation method based on a fan component bird strike test result is characterized by comprising the following steps:
step 1: acquiring bird variable parameters and fan component variable parameters;
step 2: selecting a plurality of parameters in the bird variable parameters and the fan component variable parameters in the step 1, and forming a combined matrix in which the selected parameters are combined with each other, wherein one combined parameter in each combined matrix is a group of parameter states;
and step 3: calculating a bending damage angular momentum of the bird body relative to the blade root when the bird body acts on the fan component and a twisting damage angular momentum of the bird body relative to the rotation center of the blade when the bird body acts on the fan component under the parameter state of each group in the step 2 through a formula;
and 4, step 4: comparing the bending damage angular momentum of the blade root and the torsion damage angular momentum of the rotation center of the blade, which are obtained in the step 3 and correspond to each group of parameter states in the step 2, with the limit safety angular momentum and the limit damage angular momentum respectively, so as to obtain the states of the fan component in the group of parameter states;
the torsional damage angular momentum relative to the rotation center of the blade in the step 2 is calculated by adopting the following formula:
wherein, VrelFor the resultant speed of the bird entering the engine, z is the length along the chord from the inlet edge to the center of rotation, L is the length of the bird chopped up by one rotor blade, θ is the angle of incidence of the bird's body with respect to the chord, θ' is the chord angle, ρBIs bird body density, ABIs the cross-sectional area of the bird hitting the blade.
2. The fan assembly bird strike evaluation method of claim 1 based on results of a bird strike test, wherein the bird variable parameters in step 1 comprise: bird body weight, bird body area, bird body density, bird body speed.
3. The fan assembly bird strike evaluation method of claim 1, wherein the fan assembly parameters are a rotational speed of the blades in the fan assembly, a radius of the blades in the fan assembly, and a number of the blades in the fan assembly.
4. The fan assembly bird strike evaluation method of claim 1, wherein the bird variable parameters of step 1 and the fan assembly variable parameters selected in step 2 comprise: fan speed parameter, bird body weight parameter, bird body speed parameter in the fan subassembly.
5. The fan assembly bird strike evaluation method of claim 1, wherein the bending failure angular momentum for the blade root relative to the blade root in step 2 is defined by:wherein M isBBird mass for each blade;is the velocity of failure perpendicular to the blade chord line at impact height; h is the impact height of the bird on the blade.
6. The fan assembly bird strike evaluation method of claim 5 based on results of a bird strike test, wherein the method comprisesCalculated using the following formula:wherein i is the inclination angle of the blade, α'2Is the blade exit angle;
the M isBCalculated using the following formula:
wherein,u is blade speed, VAThe birds entering the engineAxial velocity, ABProjected area of bird at engine inlet, ρBBird density.
7. The full-state bird strike assessment method based on fan assembly bird strike test results of claim 1, wherein the ultimate safe angular momentum and ultimate destructive angular momentum of step 4 are obtained through testing.
8. The fan assembly bird strike evaluation method of claim 1, wherein the condition of the fan assembly comprises the following conditions:
when the bending damage angular momentum relative to the blade root is smaller than the ultimate safe angular momentum, the fan part is in the damage standard range;
when the torsional damage angular momentum relative to the center of rotation of the blade is less than the ultimate safe angular momentum, the fan component is within the damage standard range;
when the bending damage angular momentum relative to the blade root is larger than the ultimate damage angular momentum, the fan component exceeds the damage standard range;
when the torsional failure angular momentum relative to the rotational center of the blade is greater than the ultimate failure angular momentum, the fan component will exceed the damage criteria range.
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CN104776970A (en) * 2015-04-27 2015-07-15 中国直升机设计研究所 Method for verifying bird strike resistance performance of pitch link of main blade of helicopter

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CN104776970A (en) * 2015-04-27 2015-07-15 中国直升机设计研究所 Method for verifying bird strike resistance performance of pitch link of main blade of helicopter

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