JPS5856052B2 - Annular combustor for gas turbine engine - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to gas turbine engines, and more particularly to annular combustors.

The present invention is most advantageously applicable to stationary gas turbine engines.

Gas turbine engines currently use an annular combustor located between a compressor and a turbine.

In such cases, annular combustors are often provided with longitudinal divisions, and gas turbine engines are typically assembled with stator parts sequentially and with simultaneous blade installation or turbine rotor assembly. It was manufactured by and disassembled using the reverse procedure.

This results in high effort requirements during manufacture and especially during repair.

This is because it is difficult to access the engine components for inspection and repair.

The inventor's intention is therefore to develop an annular combustor that is longitudinally divided at the dividing plane of other engine components.

In this regard, the main difficulty is caused by the flame tube of the annular combustor, which is subject to high temperatures.

The design must also be extremely robust and ensure free thermal expansion of its components.

This is because if these conditions are not met, the shape of the flame tube will be compromised, thermal stresses will occur, and the components of the flame tube will be strained and cracked, causing the annular combustor to fail. This is because both the engine and the gas turbine engine are subject to damage.

An experiment in the development of an annular combustor that compensates for the thermal expansion of individual components can be found in the annular combustor according to British Patent No. 799,605.

This conventional annular combustor has a burner device located in its inlet section and a flame tube formed by two concentric outer and inner shells.

The outer shell is longitudinally divided into a plurality of pieces, each piece having protrusions and recesses arranged alternately along the dividing line, which engage each other during assembly of the shell. A movable joint is constructed, by means of which thermal deformations of the annular combustor are partially compensated in the circumferential direction.

However, in large annular combustors, the outer shell does not have sufficient stiffness, which is characteristic of annular combustors in stationary gas turbine engines.

Other annular combustors for gas turbine engines are also known, the design of which allows the annular combustor to be split longitudinally with a split plane that matches the split plane of the turbine engine, so that the gas Easy assembly and maintenance of the turbine engine [see: Trudy Vlaskogo Turbomotorunovo Zavodaopto Sozdania Turbin
Trudy Uralskog.

turbomotornogo zaboda”0py
tsozdaniya turbin i di
zelei”) Pron Dinges on Uralsky Turbine Engine Works on the 6 Turbines and Diesels, Design and Manufacturing Experience” (Pro
cedings of UralskiiTurbin
e Engine Works on the”
Turbines and Diesels De
Signand Manufacturing Exp
erience”), 42.1972, P P-8
894).

This latter conventional annular combustor has a front burner device fixed to its inlet section and a flame tube formed by two concentric outer and inner shells with curved surfaces.

Each of the outer and inner shells is longitudinally divided into a plurality of sections, the locations of which are sealed with two plate-type sealing members.

One of the plates is a flat plate, one end of which is attached to one of the pieces and the other end left free on the other piece.

Also, one end of the other plate is attached to the piece on which the one plate is placed in a free state, and the other end surrounds the one plate and slides therewith. Form a groove joint.

A heavy frame-type load bearing device is provided for connecting the outer and inner shell pieces in the inlet section of the annular combustor, which is provided with a longitudinal division and has several heavy rings. .

At least one of the rings surrounds a piece of the outer shell and at least one other ring surrounds a piece of the inner shell.

Said ring is rigidly interconnected to a plurality of ribs, two of which are disposed in a longitudinal horizontal plane in each hand portion of the frame divider to form a divider flange; Used to secure the frame to the engine case.

A plurality of single load bearing rings are provided to connect the outer shell and inner shell sections to the exit portion of the annular combustor, which rings are also secured to the engine casing.

In such an embodiment, the load bearing device in the form of an annular frame as well as the load bearing ring are rigidly attached to the engine casing to form an integral rigid body.

During operation of an annular combustor, particularly under unstable conditions, considerable temperature differences are observed between the annular frame and the shell sections, with the result that the sections are heated relative to each other and relative to the frame. The temperature will expand.

Each piece is secured by a bracket within a ring with an annular groove.

Since the frame and the plurality of single load bearing rings are rigidly attached to the engine casing, the annular grooves and brackets serve to compensate for thermal expansion in the radial, circumferential and longitudinal directions.

Such an installation is therefore rather complex in its aspects and, moreover, fails to achieve reliable operation of the annular combustor, since in practice the necessary expansion gap is not provided.

As a result, distortion occurs in the annular combustor, for example at its inlet part,
and will suffer a loss of shape.

The purpose of the invention is to solve the above-mentioned problems of the development of an annular combustor for gas turbine engines, according to the invention the outer button and the inner shell part of the flame tube of an annular combustor In order to prevent the generation of stress due to thermal deformation and maintain a high degree of robustness of the flame tube, pieces of the flame tube shell are connected to load-bearing members.

The above problem is solved by an annular combustor for a gas turbine engine having the following configuration.

That is, the annular combustor according to the invention has a forward burner device arranged in its inlet section, a longitudinal division corresponding to the division of a gas turbine engine, and two curved surfaces.
An annular combustor FC button consisting of a flame tube formed by two concentric outer and inner shells, each shell being divided into a plurality of segments in the longitudinal direction and the segmentation locations being sealed with sealing members. an inlet portion of the annular combustor such that at least two longitudinally divided ring-shaped load bearing members are provided for each shell, one of the load bearing members being movable longitudinally and radially; and the other of the load-bearing members is arranged in the region of the outlet section of the annular combustor such that the other of the load-bearing members is movable in the radial direction, the connection of each of the shell pieces to each load-bearing member being Annular combustion characterized in that the middle part of the piece is rigidly attached to the load-bearing member and the ends of the piece are connected to the load-bearing member so as to be movable in the circumferential direction. It is a vessel.

During operation of a gas turbine engine, in an annular combustor the outer button and inner shell, the ring-shaped load bearing member and the engine casing are heated non-uniformly.

The maximum temperature is found in the outer and inner shells of the flame tube and the greatest temperature difference occurs between the outer and inner shells and the ring-shaped load-bearing member.

In order to eliminate radial temperature expansion between the outer and inner shells of the flame tube of the annular combustor and the ring-shaped load-bearing member, the shells are divided into individual pieces. A gap is then provided between the parts and sealed with a sealing member which does not impede relative expansion of the parts upon heating of the gap.

Nevertheless, such measures alone are not sufficient for reliable operation of the annular combustor.

This is because a rather complex series of relative movements during temperature expansion between the outer and inner shell parts, the ring-shaped load bearing member and the engine casing must additionally be compensated for. This is because stresses occurring in the parts of the flame tube shell as a result of thermal deformation must be eliminated and the geometry of the shell must be maintained under operating conditions.

In the annular combustor according to the invention, simple measures are used to compensate for relative movements during temperature expansion.

First of all, in order to compensate for the relative movement in the circumferential direction between the outer button and the inner shell parts, each ring-shaped load bearing member of the outer 3 and inner shell parts is In this mounting mode, the intermediate portion of the piece is rigidly fixed to the ring-shaped load bearing member, and the end portion of the piece is movable in the circumferential direction but restrained in the radial direction. The load bearing member is coupled to the load bearing member.

Secondly, for compensation of the relative movement in the longitudinal and radial direction between the ring-shaped load-bearing member and the engine casing, at least two two ring-shaped load-bearing members, one of which is disposed in the region of the inlet section of the annular combustor so that it can be moved longitudinally and radially, and the other one of which is displaceable radially at the outlet of the annular combustor. placed in the area of the part.

With this configuration, the outer and inner shell parts,
There is complete compensation for temperature expansion differences between the ring-shaped load-bearing member and the engine casing.

According to the above-described configuration, the generation of stress due to thermal deformation is prevented, and the structural robustness is increased.
This improves the reliability of the operation of the longitudinally segmented annular combustor and, with it, the reliability of the overall operation of the gas turbine engine.

Preferred embodiments of the invention will now be described in detail with reference to the accompanying drawings.

Referring to FIG. 1 of the accompanying drawings, an annular combustor 1 is mounted within a casing 2 of a gas turbine engine and arranged between a diffuser 3 of a compressor and a housing 4 of a gas turbine stator 5.

The annular combustor 1 is provided with a longitudinal division, which corresponds to that of a gas turbine engine.

The annular combustor 1 has a front burner device 6 and a flame tube 8;
The gas supply connecting member 7 is attached to the annular combustor 10 inlet portion.

The flame tube 8 is formed by two concentric shells, an outer shell 9 and an inner shell 10, which shells have a curved or cylindrical surface which is partially inclined in the direction of the gas flow to form a conical shape. It is now cylindrical.

Each of the shells 9 and 10 is divided longitudinally into pieces 11 and 12 (FIG. 2).

The dividing location is closed over its entire length with a sealing member in the form of a wave spring 13 (FIG. 3), with one end of the wave spring 13 being fixed to one of the pieces 11 and the other The ends are placed against adjacent pieces 11.

This ensures that the relative thermal expansion of the pieces is unhindered in the circumferential direction.

The sealing elements for the inner shell 10 are similar to those described above.

In order to make the wave spring 13 work better as a sealing member, a play plate 14 (FIG. 4) is provided, which is an outer piece in which one end of the wave spring 13 is placed free. It is attached to 11.

The plate 14 is placed on the corrugation of the wave spring 13 and spaced apart over a portion of the piece 11.

The outer shell 90 piece 11 and the inner shell 10 piece 12 are fixed on at least two ring-shaped load bearing members 15, 16 (FIG. 1) and 17.18, respectively.

The piece 11 is attached to the load bearing members 15, 16 (FIG. 3) in the following manner.

That is, the piece 11 in the area of the load-bearing members 15, 16 has an angle 19''J=- with their intermediate part.
and rods 20 are rigidly attached to the load bearing members 15, 16, while the ends of the pieces 11 are provided with holes 22 (FIG. 5) in which the rods 23 can be received and the load bearing members 16
The angle 21 (Figs. 5 and 6) attached to the

As is clear from FIGS. 2 to 5, the piece 11 is
During thermal expansion, it can move in the circumferential direction relative to the load bearing members 15, 16 (FIG. 3).

The manner in which the piece 12 of the inner shell 10 is attached to the ring-shaped load bearing member 17, 1B is similar to that described for the piece 11.

The arrangement of the ring-shaped load bearing members 15 to 18 (FIG. 1) is similar to that of the ring-shaped load bearing members 15 (the third
This will become clear by considering Figure).

The same applies to other matters.

The load-bearing member 15 consists of two hand parts 24''J? and 25 rigidly interconnected by an angle 26 along the split.

Each angle 26 is attached to each of the hand portions 241- and 25.

The angles 26 are connected to each other by bolts 27,
Both hand parts are rigidly connected in a separable manner.

A ring-shaped load bearing member 16,18 (FIG. 1) is located in the region of the outlet section of the annular combustor 1 and is freely movable radially relative to the housing 4 of the gas turbine stator 5.

Such a free radial movement is achieved, for example, in the case of the load-bearing member 15 by means of a bracket 28 (FIG. 7), which is attached to the housing 4 with one end thereof. It is fixed and the other end is provided with a pin which can be accommodated in the groove of the boss 29.

The fingers 30 of the pin are receivable in the radial holes 31 of the load bearing member 160.

Bracket 28 is connected to boss 29 by a finger 32 with a locking pin.

The load bearing member 18 can be freely moved in the radial direction by means of a shoulder 33 (FIG. 8) provided thereon.

The shoulder 33 is receivable within an annular groove 34 in the housing 4 to longitudinally lock the load bearing member 18 and to be free to move radially relative to the housing 4 during thermal expansion.

Thermal protection of the housing 4 is provided by a shield 35 attached to the piece 12.

The load-bearing member 15 (FIG. 1) is located in the region of the inlet section of the annular combustor 10 and is movable both longitudinally and radially relative to the casing 2.

Therefore, the load bearing member 150 is attached to the dividing surface IJ -)
37 (Fig. 9) is fixed.

The cleat 37 is placed in the socket 38 of the flange of the longitudinal division of the casing 2 with a radial gap 39 (FIG. 9) and a longitudinal gap 40.

The load-bearing member 17 (FIG. 1) is arranged in the region of the inlet section of the annular combustor 1 and is movable both longitudinally and radially relative to the diffuser 3.

Therefore, a beam IJ-) 41 is fixed to the dividing surface of the ring-shaped load bearing member 17 (eleventh).

The cleat 41 is located at 7 of the longitudinally divided portion of the diffuser 3.
A radial cap 43 (first
0) and with a longitudinal gap 44.

To increase the stiffness and strength of the inner shell 100 segments, the inner shell 10 is reinforced with additional half rings 45 and 46 (FIGS. 1 and 10), where the half rings 45 and 46 are connected to the inner shell 10 in a similar manner to the load bearing members 17 and 18.

Annular combustor 10 half ring 45 to facilitate disassembly
The controllers and 46 are not rigidly fixed to each other, but simply rest against each other at the split plane, and are radially locked with respect to each other by key joints.

In order to reduce the temperature of the diffuser 3, a shield 47 is attached between the diffuser 3 and the inner shell 10 to the load bearing members 17 and 18 and to the additional half rings 45 and 46 (FIG. 10).

[Brief explanation of drawings]

FIG. 1 is a schematic longitudinal sectional view of an annular combustor according to the invention. FIG. 2 is a sectional view taken along the line ■-■ in FIG. 1. FIG. 3 is a view taken along arrow A in FIG. FIG. 4 is an enlarged sectional view taken along line IV-IV in FIG. 3. FIG. 5 is an enlarged view of a portion B of FIG. 2. FIG. 6 is an enlarged sectional view taken along the line VT-VI in FIG. 5. FIG. 7 is an enlarged sectional view taken along the line ■-■ in FIG. 2. FIG. 8 is an enlarged view of a portion C of FIG. 1. FIG. 9 is a sectional view taken along line IX-IX in FIG. 3. FIG. 10 is a sectional view taken along line X-X in FIG. 2. FIG. 11 is a sectional view taken along the line XI-XI in FIG. 10. 1... Annular combustor, 9, 10... Shell, 11゜1
2... Part, 15, 16. 17. 18... Ring-shaped longitudinally divided load bearing member.

Claims (1)

[Claims] 1. An annular combustor for a gas turbine engine, with a forward burner device arranged in the inlet section of the annular combustor, a longitudinal division coincident with the division of the gas turbine engine, and two concentric with curved surfaces. An annular combustor consisting of a flame tube formed by an outer button and an inner shell, in which each shell is divided into a plurality of parts in the longitudinal direction, and the parts of the parts are sealed with a sealing member. , at least two ring-shaped load bearing members 15, 16, 17, 1B divided in the longitudinal direction are provided for each of the outer and inner shells 9, 100, one of the load bearing members 15, 17 being It is arranged in the region of the inlet part of the annular combustor 1 so that it can be moved longitudinally and radially and the outlet part of the annular combustor 1 is arranged so that the other load-bearing member 16, 1B can be moved radially. The connection of the sections 11, 12 of the outer and inner shells 9, 10, respectively, to the respective load-bearing members 15, 16, 17° 18 extends through the intermediate portions of the sections 11, 12. An annular combustor characterized in that it is rigidly attached to a load-bearing member and coupled to the load-bearing member so as to be movable in the circumferential direction of the ends of the section.