阅读说明：本技术 一种涡扇发动机整机高压涡轮动应力测量轴心引线结构 (Axial lead structure for measuring dynamic stress of whole high-pressure turbine of turbofan engine ) 是由 刘光远 张清 张建 霍枫 李娜 于 2021-10-25 设计创作，主要内容包括：本申请属于发动机设计技术领域,特别涉及一种涡扇发动机整机高压涡轮动应力测量轴心引线结构。该引线结构包括引线管(2),套设于低压涡轮轴(5)外侧,引线管(2)为双层管,双层管之间设置有贯穿测试线(3)的通道,引线管(2)前端在外层上设置有连通所述通道的第一引线管孔(21),第一引线管孔(21)被配置成与设置在高压压气机轴(1)上的高压压气机轴引线孔(11)对齐,引线管(2)后端在外层上设置有连通所述通道的第二引线管孔(22),第二引线管孔(22)被配置成与设置在高压涡轮轴(4)上的高压涡轮轴引线孔(41)对齐。本申请解决了双转子涡扇发动机整机高压涡轮工作叶片动应力测试轴心引线难度大、风险高的问题。(The application belongs to the technical field of engine design, and particularly relates to a complete machine high-pressure turbine dynamic stress measurement axis lead structure of a turbofan engine. This pin configuration includes that lead wire pipe (2), the cover is located low-pressure turbine shaft (5) outside, and lead wire pipe (2) are double-deck pipe, are provided with the passageway that runs through test wire (3) between the double-deck pipe, and lead wire pipe (2) front end is provided with the intercommunication on the skin first lead wire tube hole (21) of passageway, first lead wire tube hole (21) are configured into and align with high-pressure compressor shaft pin hole (11) of setting on high-pressure compressor shaft (1), and lead wire pipe (2) rear end is provided with the intercommunication on the skin second lead wire tube hole (22) of passageway, second lead wire tube hole (22) are configured into and align with high-pressure turbine shaft pin hole (41) of setting on high-pressure turbine shaft (4). The problem that the difficulty of a dynamic stress test shaft center lead of a complete machine high-pressure turbine working blade of a double-rotor turbofan engine is high and the risk is high is solved.)

1. The whole turbofan engine high-pressure turbine dynamic stress measurement axis lead structure is characterized by comprising a lead pipe (2), wherein the lead pipe (2) is sleeved outside a low-pressure turbine shaft (5), the lead pipe (2) is a double-layer pipe, a channel penetrating through a test wire (3) is arranged between the double-layer pipes, a first lead pipe hole (21) communicated with the channel is formed in the outer layer of the front end of the lead pipe (2), the first lead pipe hole (21) is configured to be aligned with a high-pressure compressor shaft lead hole (11) formed in a high-pressure compressor shaft (1) and used for leading a test lead into a measurement device of a high-pressure compressor disc cavity, a second lead pipe hole (22) communicated with the channel is formed in the outer layer of the rear end of the lead pipe (2), the second lead pipe hole (22) is configured to be aligned with a high-pressure turbine shaft lead hole (41) formed in the high-pressure turbine shaft (4), for introducing the test leads onto a high-pressure turbine disk.

2. The turbofan engine whole high pressure turbine dynamic stress measurement axial lead structure according to claim 1, wherein the lead pipe (2) is provided with a front butt joint part (23) extending into the high pressure compressor shaft (1) at a front end provided with a first lead pipe hole (21), a cross section of the front butt joint part (23) is of an annular structure, at least one first positioning boss (24) along a circumferential direction is arranged on the annular structure, a journal positioning groove is correspondingly arranged on an inner wall of the high pressure compressor shaft (1), and the first positioning boss (24) can slide in the journal positioning groove on the inner wall of the high pressure compressor shaft (1);

the rear end of the lead pipe (2) provided with the second lead pipe hole (22) is provided with a rear butt joint part (25) extending into the high-pressure turbine shaft (4), the cross section of the rear butt joint part (25) is of an annular structure, at least one second positioning boss (26) along the circumferential direction is arranged on the annular structure, the inner wall of the high-pressure turbine shaft (4) is correspondingly provided with a shaft neck positioning groove, and the second positioning boss (26) can slide in the shaft neck positioning groove in the inner wall of the high-pressure turbine shaft (4).

3. The turbofan engine complete machine high pressure turbine dynamic stress measurement axial lead structure according to claim 2, wherein a first gap is provided between the first positioning boss (24) and a journal positioning groove of the inner wall of the high pressure compressor shaft (1) along the circumferential direction; and a second clearance is formed between the second positioning boss (26) and a journal positioning groove in the inner wall of the high-pressure turbine shaft (4) along the circumferential direction, and the first clearance is smaller than the second clearance.

4. The turbofan engine complete machine high pressure turbine dynamic stress measurement axial lead structure according to claim 2, wherein a plurality of the first positioning bosses (24) are arranged on the front butt joint portion (23) at intervals along an axial direction of a lead pipe.

5. The turbofan engine whole high pressure turbine dynamic stress measurement axial lead structure according to claim 1 wherein the lead tube (2) front end extends to a high pressure compressor shaft lead hole (11) of a high pressure compressor shaft (1) at a position where a first lead tube hole (21) is provided such that the first lead tube hole (21) has a first distance from the high pressure compressor shaft lead hole (11); the rear end of the lead tube (2) extends to a high-pressure turbine shaft lead hole (41) of the high-pressure turbine shaft (4) at a position where a second lead tube hole (22) is arranged, so that a second distance is formed between the second lead tube hole (22) and the high-pressure turbine shaft lead hole (41), wherein the first distance is smaller than the second distance.

6. The axial lead structure for measuring dynamic stress of the whole turbofan engine high-pressure turbine according to claim 1, wherein the length X of the channel between the double layers of the lead tube (2) along the radial direction of the lead tube (2) is Φ H +4mm, wherein Φ H is the diameter of the test wire (3).

7. The turbofan engine complete machine high pressure turbine dynamic stress measurement axis lead structure according to claim 2, characterized in that a centering surface (27) is provided between the front end of the first positioning boss (24) of the lead tube (2) and the front end surface of the lead tube (2), and the length B of the centering surface along the axial direction of the lead tube (2) is smaller than the length a of the journal positioning slot in the high pressure compressor shaft (1).

8. The turbofan engine complete machine high pressure turbine dynamic stress measurement axial lead structure of claim 7 wherein the lead tube (2) is in close clearance fit with the inner wall of the high pressure compressor shaft (1) at the centering surface (27).

Technical Field

The application belongs to the technical field of engine design, and particularly relates to a complete machine high-pressure turbine dynamic stress measurement axis lead structure of a turbofan engine.

Background

The dynamic stress of the working blade of the high-pressure turbine of the aviation turbofan engine is an important parameter of the working blade. The dynamic stress measurement of the high-pressure turbine working blade is carried out, the stress level of the high-pressure turbine working blade in the actual working environment is accurately mastered, and the method is an important content for the development of various engines. Because the high-pressure turbine part has high working speed, high ambient temperature and complex working load, and is limited by the compact layout of the high-pressure rotor part, the structural space of the low-pressure rotor and other factors, the design difficulty of the mounting structure of the testing device and the testing lead for measuring the dynamic stress of the high-pressure turbine blade in the complete machine state is extremely high, the current common measuring method is based on the remote sensing measurement or the electrical apparatus measurement in the states of a part tester and a core machine tester, and the measuring condition of the dynamic stress of the high-pressure turbine in the complete machine state is not provided. For the dynamic stress measurement of the high-pressure turbine blade in the core machine state, a common measuring device is arranged in the core machine external space at the front end of a high-pressure compressor or the rear end of the high-pressure turbine, and a test line passes through the axle center of a high-pressure shaft and is connected to measuring equipment. The layout and the cooling environment of the testing device are greatly improved, the mounting structure of the testing line is not limited by the space structure of the low-pressure shaft under the state of the whole machine, and the realizability of the lead channel is greatly improved.

Based on the dynamic stress test of the high-pressure turbine in the complete machine state, the dynamic stress test device is generally arranged in a compressor part with relatively low temperature in consideration of the requirements of the installation environment temperature and the installation space of the test device, and a test wire needs to be led from the high-pressure turbine part to the compressor part. However, because the low-pressure turbine shaft is arranged in the high-pressure shaft, the rotating speeds of the two shafts are different, and a lead structure used in measuring the dynamic stress of the high-pressure turbine blade of the core machine cannot be adopted.

Disclosure of Invention

In order to solve the problems, the application provides an axis lead structure suitable for measuring the dynamic stress of the complete machine high-pressure turbine of a double-rotor turbofan engine, a high-vortex dynamic stress test lead channel is provided, and the dynamic stress test requirement of the complete machine high-pressure turbine is met. The lead structure design aims to solve the problems of high-pressure turbine axis space limitation, high-pressure rotor axial dimension tolerance accumulation, circumferential dimension tolerance accumulation, high-pressure rotor axis thermal deformation coordination, test lead whole-process fixation and the like, and simultaneously, the feasibility of complete machine assembly, the matching performance of a complete machine rotor system, the safety of a test, the reliability of a test signal and the like are also met.

This application turbofan engine complete machine high pressure turbine dynamic stress measures axle center pin configuration mainly includes the lead wire pipe, the low pressure turbine shaft outside is located to the lead wire pipe box, and the lead wire pipe is double-layer tube, is provided with the passageway that runs through the test wire between the double-layer tube, and the lead wire pipe front end is provided with the intercommunication on the skin the first lead wire tube hole of passageway, first lead wire tube hole are configured to align with the high pressure compressor shaft lead wire hole that sets up on the high pressure compressor shaft, are used for with the measuring device department in high pressure compressor dish chamber is introduced to the test lead wire, and the lead wire pipe rear end is provided with the intercommunication on the skin the second lead wire tube hole of passageway, second lead wire tube hole are configured to align with the high pressure turbine shaft lead wire hole that sets up on the high pressure turbine shaft, be used for with the test lead wire is introduced to on the high pressure turbine dish.

Preferably, the front end of the lead tube, which is provided with the first lead tube hole, is provided with a front butt joint part extending into the high-pressure compressor shaft, the cross section of the front butt joint part is of an annular structure, the annular structure is provided with at least one first positioning boss along the circumferential direction, the inner wall of the high-pressure compressor shaft is correspondingly provided with a journal positioning groove, and the first positioning boss can slide in the journal positioning groove on the inner wall of the high-pressure compressor shaft;

the rear end of the lead tube provided with the second lead tube hole is provided with a rear butt joint part extending into the high-pressure turbine shaft, the cross section of the rear butt joint part is of an annular structure, at least one second positioning boss is arranged on the annular structure along the circumferential direction, the inner wall of the high-pressure turbine shaft is correspondingly provided with a shaft neck positioning groove, and the second positioning boss can slide in the shaft neck positioning groove on the inner wall of the high-pressure turbine shaft.

Preferably, a first gap is formed between the first positioning boss and the journal positioning groove on the inner wall of the high-pressure compressor shaft along the circumferential direction; and a second gap is formed between the second positioning boss and the journal positioning groove on the inner wall of the high-pressure turbine shaft along the circumferential direction, and the first gap is smaller than the second gap.

Preferably, the front abutting portion is provided with a plurality of first positioning bosses at intervals in the axial direction of the lead tube.

Preferably, the lead tube front end extends toward a high pressure compressor shaft lead hole of a high pressure compressor shaft at a position where a first lead tube hole is provided, so that the first lead tube hole has a first distance from the high pressure compressor shaft lead hole; the rear end of the lead tube extends to a high-pressure turbine shaft lead hole of a high-pressure turbine shaft at a position where a second lead tube hole is arranged, so that a second distance is formed between the second lead tube hole and the high-pressure turbine shaft lead hole, wherein the first distance is smaller than the second distance.

Preferably, the length X of the channel between the double tubes of the feed-through tube in the radial direction of the feed-through tube is Φ H +4mm, where Φ H is the diameter of the test line.

Preferably, a centering surface is arranged between the front end of the first positioning boss of the lead tube and the front end surface of the lead tube, and the length B of the centering surface along the axial direction of the lead tube is smaller than the length a of the journal positioning groove in the high-pressure compressor shaft.

Preferably, the feed-through tube is in close clearance fit with the inner wall of the high-pressure compressor shaft at the centering surface.

The key points of the application are as follows:

(1) the accurate positioning structure of the lead wire path ensures the coaxiality between lead wire holes and the safety of a test wire;

(2) the whole-process reliable fixing structure of the high-pressure turbine lead pipe test lead ensures that the test wire is reliably fixed;

(3) the positioning structure of the assembling performance is improved.

The test wire is simple to install and reliable in structure, the safety of the test wire and the engine is guaranteed to the maximum extent, and the problems that the difficulty of a dynamic stress test axis lead of a complete machine high-pressure turbine working blade of a double-rotor turbofan engine is large and the risk is high are solved.

Drawings

FIG. 1 is a schematic structural diagram of a preferred embodiment of an axial lead structure for measuring dynamic stress of a whole high-pressure turbine of a turbofan engine.

FIG. 2 is a schematic diagram of a high pressure turbine lead configuration according to the embodiment of the present application shown in FIG. 1.

Fig. 3 is a schematic view of the H-direction structure of the embodiment shown in fig. 2 of the present application.

FIG. 4 is a schematic view of the circumferential positioning boss structure of the embodiment shown in FIG. 1 of the present application.

FIG. 5 is a schematic view of the cross section A-A of the embodiment shown in FIG. 4 of the present application.

FIG. 6 is a schematic view of the cross-section B-B of the embodiment shown in FIG. 4 of the present application.

Fig. 7 is a schematic view of the embodiment of the present application shown in fig. 1.

The high-pressure gas compressor comprises a high-pressure gas compressor shaft 1, a high-pressure gas compressor shaft lead hole 11, a lead pipe 2, a first lead pipe hole 21, a second lead pipe hole 22, a front butt joint part 23, a first positioning boss 24, a rear butt joint part 25, a second positioning boss 26, a centering surface 27, a test line 3, a high-pressure turbine shaft 4, a high-pressure turbine shaft 41 and a low-pressure turbine shaft 5.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. 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 some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.

In order to meet the requirements of a dynamic stress measurement test of a high-pressure turbine of a complete machine of a double-rotor turbofan engine, an axis lead structure is newly designed, and a dynamic stress test line is led to a measuring device of a disc cavity of a high-pressure compressor from a high-pressure turbine disc.

The application provides a shaft center lead structure for measuring dynamic stress of a whole high-pressure turbine of a turbofan engine, as shown in fig. 1-7, the device mainly comprises a lead tube 2, the lead tube 2 is sleeved outside a low-pressure turbine shaft 5, the lead tube 2 is a double-layer tube, a passage penetrating a test wire 3 is arranged between the double-layer tube, a first lead tube hole 21 communicated with the passage is arranged on the outer layer of the front end of the lead tube 2, the first lead tube hole 21 is configured to be aligned with a high-pressure compressor shaft lead hole 11 arranged on a high-pressure compressor shaft 1, and the rear end of the lead tube 2 is provided with a second lead tube hole 22 communicated with the channel on the outer layer, and the second lead tube hole 22 is aligned with a high-pressure turbine shaft lead hole 41 arranged on the high-pressure turbine shaft 4 and used for leading the test lead into the high-pressure turbine disc.

The utility model provides a structural scheme mainly comprises high-pressure turbine lead wire pipe and relevant location structure, and the high-pressure turbine lead wire pipe is installed in high-pressure rotor axle center, and the low pressure turbine shaft outside adopts bilayer structure, and front end and high-pressure compressor shaft cooperation department, rear end all adopt circumference location structure with high-pressure turbine shaft department, and the lead wire pipe adopts little clearance fit centering with high-pressure compressor shaft, carries out axial positioning with the high-pressure rotor through the terminal surface on the high-pressure turbine shaft.

In some alternative embodiments, referring to fig. 4-6, the lead tube 2 is provided with a front butt-joint portion 23 extending into the high-pressure compressor shaft 1 at the front end provided with the first lead tube hole 21, the cross section of the front butt-joint portion 23 is a ring structure, the ring structure is provided with at least one first positioning boss 24 along the circumferential direction, the inner wall of the high-pressure compressor shaft 1 is correspondingly provided with a journal positioning slot, and the first positioning boss 24 can slide in the journal positioning slot of the inner wall of the high-pressure compressor shaft 1;

the rear end of the lead tube 2 provided with the second lead tube hole 22 is provided with a rear butt joint part 25 extending into the high-pressure turbine shaft 4, the cross section of the rear butt joint part 25 is of an annular structure, at least one second positioning boss 26 along the circumferential direction is arranged on the annular structure, the inner wall of the high-pressure turbine shaft 4 is correspondingly provided with a shaft neck positioning groove, and the second positioning boss 26 can slide in the shaft neck positioning groove on the inner wall of the high-pressure turbine shaft 4.

In some alternative embodiments, the first positioning boss 24 and the journal positioning groove of the inner wall of the high-pressure compressor shaft 1 have a first gap M therebetween in the circumferential direction; a second clearance N is provided between the second positioning boss 26 and the journal positioning groove on the inner wall of the high-pressure turbine shaft 4 along the circumferential direction, and the first clearance M is smaller than the second clearance N.

Referring to fig. 2 and 3, the high pressure rotor is composed of a high pressure compressor rotor, a high pressure turbine rotor and a high pressure turbine lead pipe, and the high pressure compressor and the high pressure turbine rotor are connected through 5 flanges and transmit torque. After the high-pressure turbine lead pipe is installed, a box-shaped structure is formed by the high-pressure compressor rotor, the high-pressure turbine rotor and the high-pressure turbine lead pipe and is influenced by the processing tolerance accumulation and the assembly tolerance accumulation of rotor parts, and after the high-pressure turbine lead pipe is assembled in place, the risk that a first lead pipe hole 21, a high-pressure compressor shaft lead hole 11, a second lead pipe hole 22 and a high-pressure turbine shaft lead hole 41 are circumferentially staggered to block a test line exists.

Aiming at the problem, circumferential positioning boss structures are respectively designed at the matching part of the front end of the high-pressure turbine lead pipe and the high-pressure compressor shaft and the matching part of the rear end of the high-pressure turbine lead pipe and the high-pressure turbine shaft, as shown in fig. 4, and meanwhile, factors such as lead hole diameter, test line width, part processing precision and the like are comprehensively considered, a reasonable gap value M, N is set, and the alignment degree of the first lead pipe hole 21 and the high-pressure compressor shaft lead hole 11, and the alignment degree of the second lead pipe hole 22 and the high-pressure turbine shaft lead hole 41 are guaranteed.

In some alternative embodiments, as shown in fig. 4 and 7, a plurality of first positioning bosses 24 are provided on the front butt-joint portion 23 at intervals along the axial direction of the lead tube.

In some alternative embodiments, the front end of the lead tube 2 extends towards the high pressure compressor shaft lead hole 11 of the high pressure compressor shaft 1 at a position where the first lead tube hole 21 is provided, so that the first lead tube hole 21 and the high pressure compressor shaft lead hole 11 have a first distance therebetween; the rear end of the lead tube 2 extends to the high-pressure turbine shaft lead hole 41 of the high-pressure turbine shaft 4 at a position where the second lead tube hole 22 is provided, so that a second distance is provided between the second lead tube hole 22 and the high-pressure turbine shaft lead hole 41, wherein the first distance is smaller than the second distance.

After the positioning boss is added, the high-pressure rotor system is of an over-positioning structure, and therefore two measures are taken to ensure the assembly of the rotor:

first, the clearance N is enlarged to be slightly larger than the clearance M, and the lead space between the second lead pipe hole 22 and the high-pressure turbine shaft lead hole 41 is increased. The reason is that in order to ensure the safety of the test line under high-speed centrifugal load, the distance between the first lead wire tube hole 21 and the high-pressure compressor shaft lead wire hole 11DE should be shortened as much as possible, and the relatively small gap M is beneficial to reducing the risk that the first lead wire tube hole 21 and the high-pressure compressor shaft lead wire hole 11 are stuck to break the test line in assembly. Meanwhile, in order to ensure the assembly of the high-pressure turbine lead tube, the gap N is properly increased, the assembly adjusting space of the high-pressure turbine lead tube and the high-pressure turbine shaft is increased, the distance between the second lead tube hole 22 and the high-pressure turbine shaft lead hole 41 is correspondingly increased, and the test line is prevented from being blocked.

Secondly, before formal assembly, trial assembly and adjustment of the high-pressure rotor are carried out, and the influence of bolt hole gaps on accumulated tolerance of the rotor is eliminated.

In some alternative embodiments, the length X of the channel between the double tubes of the feed-through tube 2 in the radial direction of the feed-through tube 2 is Φ H +4mm, where Φ H is the diameter of the test wire 3.

Because the high-pressure turbine lead tube needs to rotate at a high speed along with the high-pressure rotor, if a test wire is fixed on the outer wall of the lead tube through the existing surface mount technology and is influenced by high-speed centrifugal force, the test wire cannot be reliably fixed, and the safety of a test is influenced, and the low-pressure turbine shaft structure is arranged on the inner wall of the lead tube, so that the installation of the test wire on the inner wall of the lead tube cannot be realized due to the influence of space. In order to solve the problem, the lead tube is designed into a double-layer structure, and the thickness X of an interlayer is phi H +4mm (phi H is the diameter of a test wire). The test wire passes through the middle of the two layers of the lead tube, and the movement of the test wire is limited by the small gap of the interlayer, so that the reliable fixation of the test wire is ensured.

In some alternative embodiments, a centering surface 27 is provided between the front end of the first positioning boss 24 of the lead tube 2 and the front end surface of the lead tube 2, and the length B of the centering surface in the axial direction of the lead tube 2 is smaller than the length a of the journal positioning groove in the high-pressure compressor shaft 1.

In some alternative embodiments, the feed-through tube 2 is fitted with a small clearance to the inner wall of the high-pressure compressor shaft 1 at the centering surface 27.

Referring to fig. 7, the high-pressure turbine lead tube is a thin and long-thin-walled tube, and is installed in the engine from the direction of the outlet of the engine, and the front end of the lead tube is always located in the blind hole of the core cavity of the core machine when the lead tube is installed. In order to ensure the stable work of the lead tube in the test, the front end of the lead tube is provided with a cylindrical surface which is matched with the inner diameter of the shaft of the high-pressure compressor by a small clearance and is centered by the cylindrical surface. If the small clearance fit surfaces contact first in the assembling process, the installation of the circumferential positioning boss is influenced.

In order to avoid the first contact of centering cylindrical surfaces in the assembling process, a centering cylindrical surface form that the length B of a centering surface along the axial direction of a lead pipe 2 is smaller than the length A of a shaft neck positioning groove in a high-pressure compressor shaft 1 is designed, so that the front end of the lead pipe in the assembling process firstly realizes the installation of a circumferential positioning boss and the shaft neck positioning groove of the compressor, the circumferential guidance of the lead pipe in the installing process is ensured, and then the radial positioning surfaces of two parts are contacted and centered, namely, a point (three) is contacted with a point (four) first in the assembling process, and the point (first) is contacted with the point (two), thereby improving the assembling performance of the lead pipe.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.