RU2525384C2 - Gas turbine engine compressor stator - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft gas turbine engine joint between compressor and combustion chamber. Gas turbine engine compressor stator comprises inner and outer housings (3) and (2), respectively, interconnected by resilient elements (6, 7). Compressor stator inner housing is coupled with combustion chamber diffuser (10) in axial direction with clearance d at butt (13) equal to 0<d<0.6 mm. Flange of combustion chamber diffuser (10) at butt (13) with compressor stator inner housing has slots (14).

EFFECT: higher reliability and efficiency, longer life.

4 dwg

Description

The invention relates to stators of compressors for gas turbine engines of aviation and ground applications.

Known compressor stator made with a front blowing cavity bounded by an elastic element and perforated shells (patent RU No. 2253046, F04D 29/58, 05.27.2005).

A disadvantage of the known design is the presence of bolted joints in the blown inner casings.

Closest to the claimed design is the stator of a compressor of a gas turbine engine made with inner and outer bodies interconnected by elastic elements (patent RU No. 2447325, F04D 29/58, 04/10/2012).

A disadvantage of the known design adopted for the prototype is that for low-mode operation it is necessary to perform axial mounting interference due to the elasticity of the shells at the joints on both sides of the blown inner stator housing and the combustion chamber diffuser, which reduces the reliability and life of the compressor for increasing operating stresses in the details of the housing.

The technical result of the claimed invention is to increase the reliability, efficiency and life of the stator and the entire engine as a whole.

The specified technical result is achieved by the fact that in the compressor stator of the gas turbine engine, including the inner and outer cases interconnected by elastic elements, the compressor stator inner case is connected to the combustion chamber diffuser in the axial direction with a gap d at the junction equal to 0 <d <0, 6 mm, while in the flange of the diffuser of the combustion chamber at the junction with the inner housing of the compressor stator grooves are made.

Docking of the compressor compressor stator inner case with the combustion chamber diffuser in the axial direction with a gap d at the joint equal to 0 <d <0.6 mm provides an interference fit during high-speed operation due to gas forces and axial thermal displacements.

The grooves in the junction in the flange of the diffuser of the combustion chamber provide a cavity between the elastic element of the compressor stator and the diffuser with a cavity in the compressor flow path, which additionally compresses the compressor housing, ensuring the tightness of the end joint of the compressor internal housing with the elastic element, which increases engine reliability.

The claimed design also allows to reduce the mass of the engine due to the fact that the diffuser of the combustion chamber during operation of the engine supports the inner housing of the compressor stator and additionally guaranteed eliminates the opening of the junction of the inner housing of the stator with an elastic element using the stop end, which allows the bolt connection to be removed in the inner housing of the compressor stator .

When docking the inner stator housing of the compressor with the diffuser of the combustion chamber in the axial direction with a gap d> 0.6 mm, gaps appear in the axial joints of the stator housings when the engine is running, which reduces the reliability of the entire engine.

Figure 1 shows a diagram of the effects of pressure loads in the stator cavities of the compressor of a gas turbine engine.

Figure 2 is a longitudinal section of the compressor stator and the combustion chamber.

In Fig.3 - element A in Fig.2 in an enlarged view (docking of the inner housing of the compressor stator with the diffuser of the combustion chamber).

Figure 4 - grooves in the flange of the diffuser.

The stator 1 of the compressor consists of the outer casing 2 and the inner casing 3. Between the casing 2 and 3 there is a rear blowing cavity 4 and a selection cavity 5. The rear blowing cavity 4 is organized, respectively, by the elastic shells 6 and 7, the outer casing 2 and the inner 3. Internal the housing 3 is joined to the elastic element 6 by means of a persistent end 8. The combustion chamber consists of a housing 9 and a diffuser 10 between which the cavity 11 is located. Between the elastic element 7 of the compressor stator 1 and the diffuser 10 of the combustion chamber is a cavity 12. Between the inner The lower case 3 of the compressor and the diffuser 10 of the combustion chamber at the joint 13 have a clearance d equal to 0 <d <0.6 mm. The size of the gap d is selected based on gas forces and thermal displacements of the inner 3 and outer 2 compressor bodies. At the junction 13 in the flange of the diffuser 10, grooves 14 are made, which communicate the cavity 12 between the elastic element 7 of the compressor stator 1 and the diffuser 10 of the combustion chamber with the cavity 15 of the compressor flow section, which additionally compresses the compressor inner case 3, ensuring the seal of the end face 8 between the inner case 3 compressors and elastic element 6.

When assembling the engine due to the elasticity of the elastic elements 6 and 7 in the end face 8 provides an interference fit for sealing at low engine operating conditions.

When the engine is running, the gap d at the junction 13 between the inner case 3 of the compressor and the diffuser 10 of the combustion chamber goes into a guaranteed interference fit due to additional compression from the combustion chamber (see Fig. 1) and a larger expansion of the inner case 3 relative to the outer (cooler) case 2 compressors, which eliminates the disclosure of junction 13 at all engine operating modes and the absence of significant loads in buildings 2 and 3, which increases the reliability of the stator and the entire engine as a whole.

Claims (1)

The stator of a compressor of a gas turbine engine, comprising an inner and an outer casing interconnected by elastic elements, characterized in that the inner casing of the compressor stator is aligned with the diffuser of the combustion chamber in the axial direction with a gap d at the junction equal to 0 <d <0.6 mm, with this in the flange of the diffuser of the combustion chamber at the junction with the inner housing of the compressor stator are grooves.

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