CN109630210B

CN109630210B - Nozzle sealing structure and aircraft engine with same

Info

Publication number: CN109630210B
Application number: CN201811545083.7A
Authority: CN
Inventors: 程瑞罡; 陈浩; 王广宁
Original assignee: AECC Shenyang Engine Research Institute
Current assignee: AECC Shenyang Engine Research Institute
Priority date: 2018-12-17
Filing date: 2018-12-17
Publication date: 2021-09-03
Anticipated expiration: 2038-12-17
Also published as: CN109630210A

Abstract

The application discloses mouthpiece seals structure, it includes rotor blade and stator blade, has protruding rotatory tooth to stator blade root at rotor blade's root, have at stator blade's root with rotatory tooth complex first order recess to and still have the second level recess in the first order recess, rotatory tooth, first order recess and second level recess constitute a mouthpiece unit of sealing. The movement direction of jet flow after throttling is changed by the mouthpiece sealing structure, the ventilation effect is reduced, the size of the mouthpiece sealing structure directly influences the change of the tooth tip throttling position and the throttling area, the influence on the labyrinth sealing performance is large, the leakage amount of the disc edge labyrinth is reduced by the mouthpiece sealing structure with the groove, and the better sealing effect is achieved; through calculation analysis and experimental verification, the design of the groove structure parameters follows the relationship of 1.23h plus or minus l, and the obtained sealing effect is better.

Description

Nozzle sealing structure and aircraft engine with same

Technical Field

The application belongs to the technical field of aeroengines, and in particular relates to a mouthpiece sealing structure and an aeroengine with the same.

Background

The nozzle sealing of the aircraft engine/gas turbine engine is a structure consisting of a cavity part below the blade root of a turbine guide blade and a working blade and the upper part of the blade, belongs to non-contact sealing, and is used for preventing or reducing mainstream high-temperature gas from entering a disc edge cavity between rotating and static discs.

As shown in fig. 1, the air flow passes through the rotor blade 10 and the stator blade 20 in order from left to right with a gap between the rotor blade 10 and the stator blade 20, and in order to prevent the air flow from flowing into the gap, a mouthpiece seal structure 30 that passes cooling air from inside to the main passage is provided between the rotor blade 10 and the stator blade 20. Normally, the mouthpiece sealing structure 30 is composed of an axial convex tooth and a corresponding concave groove, but although this structure can prevent the air flow from flowing in to some extent, the cooling air flowing into the main channel from the gap can interfere with the hot air flow in the main channel to some extent, and the aerodynamic efficiency is affected.

Disclosure of Invention

The utility model aims at providing a mouthpiece seals structure and has its aeroengine to solve any above-mentioned problem.

The technical scheme of the application is as follows: the utility model provides a mouthpiece seals structure, its includes rotor blade and stator blade, has protruding rotatory tooth to stator blade root at rotor blade's root, has at stator blade's root with rotatory tooth complex first order recess to and still have the second level recess in first order recess, rotatory tooth, first order recess and second level recess constitute a mouthpiece unit of sealing.

In the present application, the second-stage groove is rectangular.

In the present application, the depth h of the second-stage groove in the axial direction is h, the width l in the radial direction is l, and the depth h and the width l have the following relationship: l ═ 1.23 h.

In this application, the mouthpiece sealing structure includes at least one mouthpiece sealing unit.

The application also provides an aeroengine, the aeroengine includes as above any the mouthpiece seals structure.

The movement direction of jet flow after throttling is changed by the mouthpiece sealing structure, the ventilation effect is reduced, the size of the mouthpiece sealing structure directly influences the change of the tooth tip throttling position and the throttling area, the influence on the labyrinth sealing performance is large, the leakage amount of the disc edge labyrinth is reduced by the mouthpiece sealing structure with the groove, and the better sealing effect is achieved; through calculation analysis and experimental verification, the design of the groove structure parameters follows the relationship of 1.23h plus or minus l, and the obtained sealing effect is better.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

Fig. 1 is a schematic view of a prior art mouthpiece seal structure.

FIG. 2 is a schematic view of a mouthpiece seal structure applied to an aircraft engine.

Figure 3 is a schematic illustration of the dimensions of the mouthpiece seal of the present application.

Fig. 4 is an air flow simulation effect diagram of the mouthpiece sealing structure of the present application.

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 drawings in the embodiments of the present application.

As shown in FIG. 1, a rotor blade 20 is provided between two

stator blades

10, 30, the root of the rotor blade 20 has a first rotating tooth 21 and a second rotating tooth 22 at both sides in the axial direction, the root of the stator blade 10 at the previous stage has a guide vane 11 and a guide vane inner ring 12 mounted together with the guide vane 11, a first stage groove 13 and a second stage groove 14 are provided between the guide vane 11 and the guide vane inner ring 12, the first stage rotating tooth 21 extends into the first stage groove 13, and the cooling air flow flows through from bottom to top. The root of the stator blade 30 at the later stage is also provided with a guide vane 31 and a guide vane inner ring 32 which is installed together with the guide vane 31, a first-stage groove 33 and a second-stage groove 34 are arranged between the guide vane 31 and the guide vane inner ring 32, the second-stage rotating tooth 22 extends into the first-stage groove 33, and cooling air flows through from bottom to top. The rotary teeth, the first-stage grooves and the second-stage grooves form a mouthpiece sealing unit.

In the present application, the second-stage grooves 41, 34 are both rectangular grooves.

Referring to fig. 2, the second-

stage grooves

14 and 34 of the present application have a depth h in the axial direction and a width l in the radial direction, and the depth h and the width l have the following relationship: l ═ 1.23 h.

As shown in figure 3, the movement direction of jet flow after throttling is changed by the mouthpiece sealing structure, the ventilation effect is reduced, the size of the mouthpiece sealing structure directly influences the change of the tooth tip throttling position and the throttling area, and the influence on the labyrinth sealing performance is large. The sealing structure of the mouthpiece with the groove reduces the leakage amount of the grate at the edge of the disc, and has better sealing effect; through calculation analysis and experimental verification, the design of the groove structure parameters follows the relationship of 1.23h plus or minus l, and the obtained sealing effect is better.

In addition, with the structure of obturaging of the mouth of a piece in this application use aeroengine on, can play fine sealed between the rotor stator. When the specific structure is designed, the mouthpiece sealing structure with the groove can be realized only by designing the relevant parts of the 3 parts.

The utility model provides a structure of obturating of mouthpiece obtains higher level performance of obturating, realizes further reducing the leakage of system of obturating to improve gas turbine engine's performance.

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.

Claims

1. A mouthpiece seal structure is characterized by comprising rotor blades and stator blades, wherein the root of each rotor blade is provided with a rotating tooth protruding to the root of each stator blade, the root of each stator blade is provided with a first-stage groove matched with the rotating tooth, the first-stage groove is also internally provided with a rectangular second-stage groove, and the rotating tooth, the first-stage groove and the second-stage groove form a mouthpiece seal unit, wherein the depth of the second-stage groove in the axial direction is h, the width of the second-stage groove in the radial direction is l, and the depth h and the width l have the following relation: l ═ 1.23 h.

2. The mouthpiece seal structure of claim 1, wherein the mouthpiece seal structure includes at least one mouthpiece seal unit.

3. An aircraft engine, characterized in that it comprises a mouthpiece seal structure according to any of claims 1 to 2.