JP4529521B2 - Blade swing control device for compressor, blade swing control device for fan, compressor, and fan - Google Patents

Description

  The present invention relates to a compressor and a fan, which are elements of a jet engine, and more particularly to a compressor blade swing control device and a fan blade swing that control swing motions of a variable stationary blade and a variable guide blade. The present invention relates to a control device.

  A jet engine mounted on a high subsonic speed machine has a compressor as one of the elements, and this compressor compresses air taken into an engine flow path formed in an engine case in the jet engine. The general configuration is as follows.

  That is, in the engine case, a plurality of stages of compressor rotors are provided along the engine axial direction, and each compressor rotor is configured to be rotatable about the engine axis, A plurality of blades are provided in the circumferential direction. In the engine case, a plurality of stages of compressor stators are provided alternately with the plurality of stages of compressor rotors along the engine axial direction, and each of the compressor stators has the engine flow path. A plurality of variable stator vanes capable of swinging in an opening / closing direction (opening direction / closing direction) for opening and closing are provided in the circumferential direction. Further, a guide stator is provided on the front side (inlet side) of the compressor rotor at the foremost stage in the engine case, and the guide stator has a plurality of variable guide vanes that can swing in the opening / closing direction. Is provided in the circumferential direction.

  The engine case is provided with a plurality of actuators for swinging all the variable stator blades and all the variable guide blades in synchronization with the opening / closing direction. Here, the plurality of actuators are controlled in accordance with the corrected rotation speed of the compressor rotor.

  Therefore, by rotating the compressor rotors in a plurality of stages, the air taken into the engine flow path is rectified by the guide stator and the compressor stators in the plurality of stages, and the compressor rotors in a plurality of stages and the plurality of compressor rotors are rectified. The compressor can be compressed by cooperation of the compressor stator of the stage (the guide stator). On the other hand, by controlling a plurality of the actuators according to the corrected rotation speed of the compressor rotor, laminar flow separation due to interference with the shock wave of the rear moving blade is suppressed on the variable stationary blade and the variable guide blade. However, a sufficient flow rate of air can be sent backward.

In addition, there exist some which are shown to patent document 1 and patent document 2 as a prior art relevant to this invention.
JP 2002-310100 A JP 2000-46688 A

  By the way, the flight altitude of the high subsonic aircraft at the time of cruising usually reaches about 10000 m, but when the flight altitude of the high subsonic aircraft further increases, the aerodynamic load of the moving blade increases rapidly, In some cases, the jet engine may operate in an unstable manner leading to a stall phenomenon.

  Heretofore, there has been no sufficient knowledge about the relationship between the flight altitude of the high subsonic aircraft and the aerodynamic load of the moving blade. Further, the above-described problem occurs not only in the compressor but also in a fan with a fan guide stator.

  Accordingly, the present invention provides a novel configuration of a blade oscillating control device for a compressor based on new knowledge obtained in relation to the flight altitude of the high subsonic aircraft and the aerodynamic load of the moving blade, It is an object of the present invention to provide a fan blade swing control device, a compressor having a novel configuration, and a fan having a novel configuration.

In the first aspect of the present invention, it is used in a compressor that is one of the elements of a jet engine, and all the variable stator blades in a multi-stage compressor stator and the front side of the front-stage compressor rotor are used. In the compressor blade swing control device for controlling the swing operation of all the variable guide blades in the guide stator arranged in
First swinging means for swinging all the variable stator vanes in synchronization with an opening / closing direction (opening / closing direction) for opening / closing an engine flow path of the jet engine;
Second swinging means for swinging all the variable guide vanes in synchronization with the opening and closing direction;
Reference data representing a reference characteristic curve of a target swing angle of the variable stationary blade or the variable guide blade in the opening / closing direction and a corrected rotation speed of the compressor rotor is stored, and a predetermined flight having a flight altitude of 10,000 m or more is stored. When the altitude is exceeded, only the portion of the compressor rotor corresponding to the air inlet tip side relative Mach number 1.2 that is higher than the corrected rotation speed is deformed in the closing direction with respect to the reference characteristic curve. Storage means for storing deformation data representing a curve;
Based on the reference characteristic curve, target swing angles of all the variable stationary blades are acquired from the corrected rotation speed of the compressor rotor, and the compressor rotor is corrected based on the reference characteristic curve or the deformation characteristic curve. Target swing angle acquisition means for acquiring target swing angles of all the variable guide vanes from the rotational speed and the flight altitude;
The first swinging means is controlled so that the swing angles of all the variable stationary blades become the target swing angle, and the swing angles of all the variable guide blades become the target swing angle. Control means for controlling the second swing means;
It is characterized by comprising.

  Here, the blade swing control device has an inlet tip side relative Mach number of 1.2 or more, and when the Reynolds number (inlet Reynolds number) on the inlet side of the variable guide blade is reduced, in other words, the compression When the corrected rotational speed of the aircraft rotor is equal to or higher than the corrected rotational speed corresponding to the inlet tip side relative Mach number 1.2 and the flight altitude is increased, the aerodynamic load of only the first stage blades increases rapidly. It was invented based on knowledge.

  According to the first aspect of the invention, the storage unit stores in advance the reference data representing the reference characteristic curve and the deformation data representing the deformation characteristic curve. Then, the target swing angle acquisition means acquires all the variable swing vane target swing angles from the corrected rotation speed of the compressor rotor based on the reference characteristic curve, while the control means acquires all the variable swings. The first swinging means is controlled such that the swing angle of the stationary blade becomes the target swing angle. Further, while acquiring the target swing angle of all the variable guide vanes from the corrected rotation speed and the flight altitude of the compressor rotor based on the reference characteristic curve or the deformation characteristic curve by the target swing angle acquisition means, The second swinging means is controlled by the control means so that the swing angles of all the variable guide vanes become the target swing angle. Thereby, it is possible to control the swinging motion of all the variable vanes and all the variable guide vanes.

  Here, when the flight altitude exceeds a predetermined flight altitude of 10000 m or more, the deformation characteristic curve is for a portion equal to or higher than the corrected rotation speed of the compressor rotor corresponding to an air inlet tip side relative Mach number of 1.2. Only the reference characteristic curve is deformed in the closing direction, and all the variable guides are derived from the corrected rotation speed and flight altitude of the compressor rotor based on the reference characteristic curve or the deformation characteristic curve. Since the target swing angle of the wing is acquired, even if the relative Mach number on the air inlet tip side is 1.2 or more and the flight altitude exceeds a predetermined flight altitude of 10,000 m or more, the variable guide wing is The occurrence of laminar flow separation can be suppressed.

In the invention according to claim 2, it is used for the fan which is one of the elements of the jet engine, and is arranged on the front side of all the variable stator blades in the multi-stage fan stator and the front-stage fan rotor. In the fan blade swing control device for controlling the swing operation of all the variable guide blades in the fan guide stator,
First swinging means for swinging all the variable stator vanes in synchronization with an opening / closing direction (opening / closing direction) for opening / closing an engine flow path of the jet engine;
Second swinging means for swinging all the variable guide vanes in synchronization with the opening and closing direction;
Reference data representing a reference characteristic curve of a target swing angle of the variable stationary blade or the variable guide blade in the opening / closing direction and a corrected rotational speed of the fan rotor is stored, and a predetermined flight height of 10,000 m or higher is stored. In the case of exceeding the reference characteristic curve, deformation data representing the deformation characteristic curve deformed in the closing direction is stored only for the portion of the fan rotor corresponding to the Mach number 1.2 that is equal to or greater than the corrected rotation speed. Storage means;
Based on the reference characteristic curve, the target swing angle of all the variable stator vanes is acquired from the corrected rotation speed of the fan rotor, and the corrected rotation speed of the fan rotor is calculated based on the reference characteristic curve or the deformation characteristic curve. And target swing angle acquisition means for acquiring target swing angles of all the variable guide vanes from the flight altitude;
The first swinging means is controlled so that the swing angles of all the variable stationary blades become the target swing angle, and the swing angles of all the variable guide blades become the target swing angle. Control means for controlling the second swing means;
It is characterized by comprising.

  Here, in the blade swing control device, when the inlet tip side relative Mach number is 1.2 or more and the Reynolds number (inlet Reynolds number) on the inlet side of the variable guide blade decreases, in other words, the fan A novel finding that the aerodynamic load of only the first stage blade increases rapidly when the corrected rotational speed of the rotor is equal to or higher than the corrected rotational speed corresponding to the inlet tip side relative Mach number 1.2 and the flight altitude increases. It was invented based on this.

  According to the invention specific matter described in claim 2, the storage means stores the reference data representing the reference characteristic curve and the deformation data representing the deformation characteristic curve in advance. Then, while acquiring the target swing angle of all the variable stationary blades from the corrected rotation speed of the fan rotor based on the reference characteristic curve by the target swing angle acquiring means, all the variable static blades are acquired by the control means. The first swinging means is controlled so that the swing angle of the blades becomes the target swing angle. Further, while acquiring the target swing angle of all the variable guide vanes from the corrected rotation speed and flight altitude of the fan rotor based on the reference characteristic curve or the deformation characteristic curve by the target swing angle acquisition means, The second swinging means is controlled by the control means so that the swing angles of all the variable guide vanes become the target swing angle. Thereby, it is possible to control the swinging motion of all the variable vanes and all the variable guide vanes.

  Here, the deformation characteristic curve is only for a portion of the fan rotor that exceeds the corrected rotation speed corresponding to the air inlet tip side relative Mach number of 1.2 when the flight altitude exceeds a predetermined flight altitude of 10,000 m or more. The reference characteristic curve is deformed in the closing direction, and all of the variable guide vanes are determined from the corrected rotation speed and flight altitude of the fan rotor based on the reference characteristic curve or the deformation characteristic curve. Since the target swing angle is acquired, even if the relative Mach number on the air inlet tip side is 1.2 or more and the flight altitude exceeds a predetermined flight altitude of 10,000 m or more, the laminar flow is applied to the variable guide wing. It can suppress that peeling arises.

In the invention according to claim 3, in the compressor which is one of the elements of the jet engine and compresses the air taken into the engine flow path formed in the engine case in the jet engine,
A plurality of compressor rotors provided along the engine axial direction in the engine case, each configured to be rotatable about the engine axis, and each having a plurality of rotor blades in the circumferential direction;
A plurality of stages of compressor stators provided alternately with a plurality of stages of compressor rotors along the engine axial direction in the engine case, each having a plurality of variable stator vanes in the circumferential direction;
A guide stator provided on the front side of the foremost compressor rotor in the engine case and provided with a plurality of variable guide vanes in the circumferential direction;
A blade swing control apparatus for a compressor comprising the invention-specifying matters of claim 1;
It is characterized by comprising.

  According to the invention specific matter of claim 3, in addition to the action of the invention specific matter of claim 1, by rotating the compressor rotor in a plurality of stages, the air taken into the engine flow path is While being rectified by the guide stator and a plurality of stages of compressor stators, compression can be achieved by cooperation of the plurality of stages of compressor rotors and a plurality of stages of compressor stators (the guide stator).

The invention according to claim 4 is a jet engine fan which is one of the elements of a jet engine and takes air into an engine flow path formed in an engine case of the jet engine.
A fan rotor provided in the engine case, configured to be rotatable about an engine axis, and provided with a plurality of rotor blades in the circumferential direction;
A fan stator provided on the rear side of the fan rotor in the engine case and provided with a plurality of stationary blades in the circumferential direction;
A fan guide stator provided on the front side of the fan rotor in the engine case and provided with a plurality of variable guide vanes;
A fan blade swing control device comprising the specific matters of the invention according to claim 2;
It is characterized by comprising.

  According to the invention specific matter of claim 4, by rotating the fan rotor of a plurality of stages, the air is rectified by the guide stator and the compressor stator of the plurality of stages and is taken into the engine flow path. Can do.

  According to the invention described in any one of claims 1 to 4, the predetermined flight altitude where the air inlet tip side relative Mach number is 1.2 or more and the flight altitude is 10,000 m or more. Even if the altitude exceeds the altitude, it is possible to suppress the laminar flow separation on the variable guide vane. Therefore, when the high subsonic speed rises to the high altitude, the aerodynamic load of the moving blade It is possible to prevent the jet engine from operating unstablely leading to a stall phenomenon without increasing rapidly.

  Hereinafter, with reference to the drawings, the general configuration of the compressor according to the best mode of the present invention, the new knowledge obtained about the relationship between the flight altitude of the high subsonic aircraft and the aerodynamic load of the moving blade, and this new The novel configuration of the compressor blade swing control device based on this knowledge will be sequentially described. Note that “front and rear” refers to the left and right in FIG. 1 with reference to the orientation at the time of publication of the patent publication.

  As shown in FIG. 1, a compressor (high pressure compressor) 1 according to the best mode of the present invention is one of the elements of a jet engine mounted on a high subsonic speed machine, and an engine case in the jet engine. The air sent into the engine flow path 3 formed in 2 is compressed. The general configuration of the compressor 1 is as follows.

  That is, a plurality of stages (two stages in the best mode of the present invention) of compressor rotors 4a and 4b are provided in the engine case 2 along the engine axial direction (left-right direction in FIG. 1). Each of the compressor rotors 4a and 4b is configured to be rotatable about the engine axis, and includes a plurality of rotor blades 5a and 5b (only one is shown in FIG. 1) in the circumferential direction. Yes. Here, the multistage compressor rotors 4a and 4b are integrally connected to a multistage turbine rotor (not shown) in the jet engine turbine.

  Further, in the engine case 2, a plurality of stages (two stages in the best mode of the present invention) of compressor stators 6a and 6b alternate with a plurality of stages of compressor rotors 4a and 4b along the engine axial direction. Each of the compressor stators 6a and 6b is provided with a plurality (only one is shown in FIG. 1) of variable stator blades 7a and 7b in the circumferential direction. Here, each of the variable stator vanes 7a and 7b is configured to be swingable via a swing shaft 8 in an opening / closing direction (opening / closing direction) for opening and closing the engine flow path 3 (FIG. 3). The engine case 2 is provided with a plurality of first actuators 9 (only one is shown in FIG. 1) that swings all the variable stator vanes 7a and 7b in synchronization with the opening and closing direction.

  Further, a guide stator 10 is provided on the front side (inlet side) of the compressor rotor 4a at the foremost stage in the engine case 2, and the guide stator 10 includes a plurality of variable guide vanes 11 in the circumferential direction. ing. Here, each variable guide vane 11 is configured to be swingable via the swing shaft 12 in the opening and closing direction (see FIG. 3), and all the variable guide vanes 11 are provided in the engine case 2. There are provided a plurality of second actuators 13 (only one is shown in FIG. 1).

  The rotor blade 5a of the compressor rotor 4a at the foremost stage is referred to as a first stage rotor blade, and the rotor blade 5b of the compressor rotor 4b at the second stage is referred to as a second stage rotor blade. Similarly, the variable stator blade 7a of the compressor stator 6a in the foremost stage is referred to as a one-stage variable stator blade, and the variable stator blade 7b of the two-stage compressor stator 6b is referred to as a two-stage variable stator blade.

Therefore, by driving the jet engine turbine to rotate the compressor rotors 4a and 4b in a plurality of stages integrally with the turbine rotors in a plurality of stages, the air taken into the engine flow path 3 is guided to the guide stator 10 and While being rectified by a plurality of stages of compressor stators 6a and 6b, the compressor rotors 4a and 4b of a plurality of stages and the compressor stators 6a and 6b (guide stators 10) of the plurality of stages can be compressed. The novel knowledge obtained about the relationship between the flight altitude of the high subsonic aircraft and the aerodynamic loads of the moving blades 5a and 5b will be described.

  In obtaining this new knowledge, a Reynolds number change test was conducted using a simulated compressor element (not shown) simulating the compressor 1. This Reynolds number change test is performed by comparing the air inlet tip side relative Mach number (M = 0.8, M = 1.2, M = 1.35) as seen from the inlet of the first stage blade 5a (second stage blade 5b). This is a test for examining the variation of the aerodynamic load of the first stage moving blade 5a (second stage moving blade 5b) accompanying the change of the Reynolds number (inlet Reynolds number) Re on the inlet side of the variable guide blade 11.

  Based on the test result of the Reynolds number change test, the relationship between the inlet Reynolds number Re of the variable guide blade 11 and the aerodynamic load of the first stage blade 5a is summarized as shown in FIG. The relationship between the Reynolds number Re and the aerodynamic load of the two-stage rotor blade 5b is summarized as shown in FIG. The aerodynamic load in FIGS. 4 and 5 is a value obtained by making the static pressure difference between the inlet and the outlet of the first stage blade 5a (two stage blade 5b) dimensionless.

  From the test results shown in FIG. 4, when the inlet tip side relative Mach number is 1.2 or more and the inlet Reynolds number of the variable guide vane 11 becomes small, the aerodynamic load of the first stage moving blade 5a increases rapidly. It has been found. On the other hand, from the test results shown in FIG. 5, even if the inlet tip side relative Mach number is 1.2 or more and the inlet Reynolds number of the variable guide blade 11 decreases, the aerodynamic load of the two-stage rotor blade 5b changes. It has been found that the aerodynamic load variation phenomenon of the first stage blade 5a is not reflected in the subsequent aerodynamic load of the second stage blade 5b.

  Therefore, when the inlet tip side relative Mach number is 1.2 or more and the inlet Reynolds number becomes smaller, in other words, the corrected rotation speed of the compressor rotors 4a and 4b corresponds to the inlet tip side relative Mach number 1.2. When the flying speed is higher than the corrected rotational speed, the laminar flow separation occurs in the variable guide blade 11 due to the interference with the shock wave from the first stage moving blade 5a, and the aerodynamic load of only the first stage moving blade 5a suddenly increases. (New knowledge about the relationship between the flight altitude of the high subsonic aircraft and the aerodynamic load of the moving blades 5a, 5b).

  Next, the compressor blade swing controller 14 having a novel configuration based on the novel knowledge will be described.

  The compressor blade swing control device 14 controls swing operations of all the variable stationary blades 7a and 7b and all the variable guide blades 11, and includes the plurality of first actuators 9 and the plurality of first actuators 9 described above. In addition to the two actuators 13, a storage unit 15 (database), a target swing angle acquisition unit 16, and a control unit 17 are provided. And the specific content of the memory | storage part 15, the target rocking angle acquisition part 16, and the control part 17 is as follows.

  That is, as shown in FIG. 2, the storage unit 15 stores a reference characteristic curve between the target swing angle of the variable stationary blades 7a, 7b or the variable guide blades 11 in the opening / closing direction and the corrected rotational speed of the compressor rotors 4a, 4b. Reference data indicating BC is stored. The corrected rotational speeds of the compressor rotors 4a and 4b are the rotational speeds of the compressor rotors 4a and 4b in consideration of the total temperature at the inlet of the compressor 1, and the compressor rotors 4a and 4b in FIG. For the sake of convenience, the corrected rotation speed is expressed as% rotation relative to the rated rotation speed.

  When the flight altitude exceeds 10000 m, the storage unit 15 provides a reference in accordance with the flight altitude only for the portions of the compressor rotors 4a and 4b corresponding to the air inlet tip side relative Mach number of 1.2 or higher. Deformation data indicating deformation characteristic curves DC1, DC2, DC3 deformed in the closing direction with respect to the characteristic curve BC is stored. In the best mode of the present invention, the portion of the compressor rotors 4a and 4b corresponding to the air inlet tip side relative Mach number 1.2 is equal to or greater than 90% rotation in the best mode of the present invention. That means.

  Here, the deformation characteristic curve DC1 is a deformation characteristic curve when the flight altitude is higher than 10000 m and 15000 m or less, and draws the same locus as the reference characteristic curve BC up to 90% rotation. The deformation characteristic curve DC2 is a deformation characteristic curve when the flight altitude is higher than 15000 m and less than or equal to 20000 m, and draws the same trajectory as the reference characteristic curve BC up to 90% rotation. The above portion is deformed in the closing direction with respect to the deformation characteristic curve DC1. Further, the deformation characteristic curve DC2 is a deformation characteristic curve when the flight altitude is higher than 20000 m and less than or equal to 24000 m, and draws the same trajectory as the reference characteristic curve BC up to 90% rotation. The above portion is deformed in the closing direction with respect to the deformation characteristic curve DC2.

  The target swing angle acquisition unit 16 acquires target swing angles of all the variable stationary blades 7a and 7b from the corrected rotational speeds of the compressor rotors 4a and 4b based on the reference characteristic curve BC. Further, the target swing angle acquisition unit 16 calculates the target swing of all the variable guide vanes 11 from the corrected rotation speed and the flight altitude of the compressor rotors 4a and 4b based on the reference characteristic curve BC or the deformation characteristic curves DC1, DC2, and DC3. The moving angle is acquired. The corrected rotational speeds and flight altitudes of the compressor rotors 4a and 4b are detected by appropriate sensors (not shown), but the specific correction rotational speeds and flying altitudes of the compressor rotors 4a and 4b are specific. A description of the detection mode is omitted.

  The control unit 17 controls the plurality of first actuators 9 so that the swing angles of all the variable stationary blades 7a and 7b become the target swing angle. The control unit 17 controls the second actuator 13 so that the swing angles of all the variable guide vanes 11 become the target swing angle.

  Next, the operation and effect of the best mode of the present invention will be described.

  The storage unit 15 stores in advance reference data indicating the reference characteristic curve BC and deformation data indicating the deformation characteristic curves DC1, DC2, and DC3. The target swing angle acquisition unit 16 acquires the target swing angles of all the variable stationary blades 7a and 7b from the corrected rotational speeds of the compressor rotors 4a and 4b based on the reference characteristic curve BC, while the control unit 17 The first actuator 9 is controlled so that the swing angles of all the variable stationary blades 7a and 7b become the target swing angle. Further, the target swing angle acquisition unit 16 performs the target swing of all the variable guide vanes 11 from the corrected rotation speed and the flight altitude of the compressor rotors 4a, 4b based on the reference characteristic curve BC or the deformation characteristic curves DC1, DC2, DC3. While acquiring the angle, the controller 17 controls the second actuator 13 so that the swing angle of all the variable guide vanes 11 becomes the target swing angle. As a result, the swinging motion of all the variable stator vanes 7a and 7b and all the variable guide vanes 11 can be controlled.

  Here, the deformation characteristic curves DC1, DC2, and DC3 are equal to or higher than the corrected rotation speed of the compressor rotors 4a and 4b corresponding to the air inlet tip side relative Mach number 1.2 when the flight altitude exceeds a predetermined flight altitude. Only the portion is deformed in the closing direction with respect to the reference characteristic curve BC, and the corrected rotational speeds of the compressor rotors 4a and 4b are based on the reference characteristic curve BC or the deformation characteristic curves DC1, DC2, and DC3. Since the target swing angles of all the variable guide vanes 11 are obtained from the flight altitude, the air inlet tip side relative Mach number is 1.2 or more, the flight altitude exceeds 10,000 m and is around 20000 m (18000 m). 22000 m), laminar separation can be prevented from occurring in the variable guide vane 11.

  As described above, according to the best mode of the present invention, even if the air inlet tip side relative Mach number is 1.2 or more and the flight altitude exceeds 10000 m and reaches around 20000 m, the variable guide wing 11 is provided. Since the occurrence of laminar flow separation can be suppressed, the aerodynamic load of the moving blades 5a and 5b does not increase rapidly when the high subsonic aircraft ascends to a flight altitude of about 20000 m. It is possible to avoid an unstable operation that leads to a stall phenomenon of the engine.

  Further, the present invention is not limited to the description of the best mode of the invention described above, and the compressor is based on novel knowledge about the relationship between the flight altitude of the high subsonic aircraft and the aerodynamic load of the moving blades 5a and 5b. It is also possible to apply the novel configuration of the blade oscillating control device 14 to a fan blade oscillating control device (not shown) used for a fan that is one of the elements of the jet engine. In some cases, the same effects as those described above can be obtained.

  Here, although not shown in the figure, the fan has a fan rotor having the same configuration as the compressor rotors 4a and 4b, a fan stator having the same configuration as the compressor stators 6a and 6b, and a fan similar to the guide stator 10. And a guide stator. The fan blade swing control device controls swing operations of all variable stationary blades in the fan stator and all variable guide blades in the fan guide stator.

It is a typical fragmentary sectional view of the compressor concerning the best form of the present invention. It is a figure which shows the reference | standard characteristic curve and deformation | transformation characteristic curve of a target rocking | fluctuation angle and the correction rotation speed of a fan rotor. It is a figure explaining the relationship of a variable stationary blade, a variable guide blade, or a moving blade with respect to the longitudinal direction of an engine flow path. It is a figure which shows the relationship between the inlet Reynolds number of a guide blade, and the aerodynamic load of a 1 stage moving blade. It is a figure which shows the relationship between the inlet Reynolds number of a guide blade, and the aerodynamic load of a two-stage moving blade.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Compressor 2 Engine case 3 Engine flow path 4a, 4b Compressor rotor 5a, 5b Rotor blade 6a, 6b Compressor stator 7a, 7b Variable stator blade 9 First actuator 10 Guide stator 11 Variable guide blade 13 Second actuator 14 Compression Machine blade swing control device 15 Storage unit 16 Target swing angle acquisition unit 17 Control unit

Claims (4)

It is used for a compressor that is one of the elements of a jet engine, and includes all the variable stator vanes in a multi-stage compressor stator and all the variable guide vanes in a guide stator disposed in front of the front-stage compressor rotor. In the compressor blade swing control device for controlling the swing operation,
First swinging means for swinging all the variable stator vanes in synchronization with an opening / closing direction (opening / closing direction) for opening / closing an engine flow path of the jet engine;
Second swinging means for swinging all the variable guide vanes in synchronization with the opening and closing direction;
Reference data representing a reference characteristic curve of a target swing angle of the variable stationary blade or the variable guide blade in the opening / closing direction and a corrected rotation speed of the compressor rotor is stored, and a predetermined flight having a flight altitude of 10,000 m or more is stored. When the altitude is exceeded, only the portion of the compressor rotor corresponding to the air inlet tip side relative Mach number 1.2 that is higher than the corrected rotation speed is deformed in the closing direction with respect to the reference characteristic curve. Storage means for storing deformation data representing a curve;
Based on the reference characteristic curve, target swing angles of all the variable stationary blades are acquired from the corrected rotation speed of the compressor rotor, and the compressor rotor is corrected based on the reference characteristic curve or the deformation characteristic curve. Target swing angle acquisition means for acquiring target swing angles of all the variable guide vanes from the rotational speed and the flight altitude;
The first swinging means is controlled so that the swing angles of all the variable stationary blades become the target swing angle, and the swing angles of all the variable guide blades become the target swing angle. Control means for controlling the second swing means;
A compressor blade swing control device characterized by comprising: Used for a fan, which is one of the elements of a jet engine, swings of all variable stator blades in a multi-stage fan stator and all variable guide blades in a fan guide stator arranged in front of the front fan rotor In a fan blade swing control device for controlling the operation,
First swinging means for swinging all the variable stator vanes in synchronization with an opening / closing direction (opening / closing direction) for opening / closing an engine flow path of the jet engine;
Second swinging means for swinging all the variable guide vanes in synchronization with the opening and closing direction;
Reference data representing a reference characteristic curve of a target swing angle of the variable stationary blade or the variable guide blade in the opening / closing direction and a corrected rotational speed of the fan rotor is stored, and a predetermined flight height of 10,000 m or higher is stored. In the case of exceeding the reference characteristic curve, deformation data representing the deformation characteristic curve deformed in the closing direction is stored only for the portion of the fan rotor corresponding to the Mach number 1.2 that is equal to or greater than the corrected rotation speed. Storage means;
Based on the reference characteristic curve, the target swing angle of all the variable stator vanes is acquired from the corrected rotation speed of the fan rotor, and the corrected rotation speed of the fan rotor is calculated based on the reference characteristic curve or the deformation characteristic curve. And target swing angle acquisition means for acquiring target swing angles of all the variable guide vanes from the flight altitude;
The first swinging means is controlled so that the swing angles of all the variable stationary blades become the target swing angle, and the swing angles of all the variable guide blades become the target swing angle. Control means for controlling the second swing means;
A fan blade swing control device characterized by comprising: One of the elements of a jet engine, wherein the compressor compresses air taken into an engine flow path formed in an engine case in the jet engine.
A plurality of compressor rotors provided along the engine axial direction in the engine case, each configured to be rotatable about the engine axis, and each having a plurality of rotor blades in the circumferential direction;
A plurality of stages of compressor stators provided alternately with a plurality of stages of compressor rotors along the engine axial direction in the engine case, each having a plurality of variable stator vanes in the circumferential direction;
A guide stator provided on the front side of the foremost compressor rotor in the engine case and provided with a plurality of variable guide vanes in the circumferential direction;
A blade swing control apparatus for a compressor comprising the invention-specifying matters of claim 1;
The compressor characterized by comprising. One of the elements of a jet engine, in a fan for a jet engine that takes air into an engine flow path formed in an engine case in the jet engine,
A fan rotor provided in the engine case, configured to be rotatable about an engine axis, and provided with a plurality of rotor blades in the circumferential direction;
A fan stator provided on the rear side of the fan rotor in the engine case and provided with a plurality of stationary blades in the circumferential direction;
A fan guide stator provided on the front side of the fan rotor in the engine case and provided with a plurality of variable guide vanes;
A fan blade swing control device comprising the specific matters of the invention according to claim 2;
The fan characterized by comprising.

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