DE1428223A1 - Compressor for gas turbine jet engine - Google Patents

Description

i ^J atentamv5 ,! »!

DIpI. ed. C.7 .'-.! Ic-Ch

Dipl. Inn. G. Λ-jch

Dr. T. Hj-.Ssch

Kaufingerstr. 8, Tel. 240 275 V ^^ ROHS-ROYCl HMITED 1428223

Hightingale Road, Derby, England.

Compressor for gas turbine jet engine.

The invention relates to a compressor for a gas turbine jet engine, comprising a cylindrical outer housing and a cylindrical inner housing which is inside of the outer housing and attached to it and which has a series of rings following one another in the axial direction, each of which has at least one Carrying stage of stator blades, these rows of rings a plurality of one another in the axial direction include the following undivided rings, which are arranged on the upstream part of the compressor, and at least a ring disposed on the downstream part of the compressor and in a substantially axial direction is split, the or each split ring having support means directly connected to the outer housing are that they lean on it.

J 90 9R ^ sZn-SC

H28223

Preferably at least one of the undivided rings is with the outer housing nmr via its connection with the neighboring ones Wrestling connected.

Preferably is on the downstream part of the compressor a plurality of divided rings following one another in the axial direction is provided.

The split ring, or at least one of the same, can be provided with a flange which forms the support means and which is equipped with an edge which engages in a groove in the outer housing. The or äeo.er splash is preferably cut out in order to increase its elasticity so that these divided rings can adapt to the shape of the outer housing.

In a preferred embodiment, at least one of the stages of the compressor consists of stator blades with platforms, which by brazing or welding, in accordingly shaped slots of the associated rings are attached.

Preferably the radial thickness of the platforms is substantial same as the radial thickness of the associated rings ·.

's.

At least one of the stages can consist of stator blades ^ which are provided with platforms, which are connected by brazing or welding so that they the ring or a

H28223

Form part of it. By. Hard solder or welding together connected platforms lying next to one another are preferably designed in such a way that air outlets between them be formed, through which part of the air compressed in the compressor can be discharged from it, means are provided to control the discharge of compressed air through these openings.

The invention also includes a gas turbine jet engine equipped with such a compressor. The compressor can be the high-pressure compressor and the engine can be a bypass engine which has a low-pressure compressor which releases part of the compressed air it has compressed through a bypass line. The arrangement here can be such that air flowing through the air outlet openings is released to the bypass line.

Further advantages and characteristics of the invention emerge from the following description by way of example with reference to the accompanying drawings.
1 is a partially cross-sectional side elevation of a gas turbine jet engine equipped with a compressor according to the invention;

Fig. 2 is a broken cross-section showing the high pressure compressor on a larger scale,

Fig. 3 is a fragmentary diagram viewed in the direction the arrow 3 in Fig. 2,

909828 / 03ßß

Flg. Figure 4 is a broken-away elevation taken along line 4-4 in Fig. 2 and

Figures 5 and 6 show broken away diagrams of parts of the structure according to Fig. 2 in an exploded view

A bypass gas turbine jet engine used to propel an aircraft IO has an engine housing 11, comprising, in the direction of flow, a low-pressure compressor 12, a high-pressure compressor 13, and a combustion system 14 and high pressure and low pressure turbines 15, wherein the turbine exhaust gases exit to the outside air through an exhaust pipe, which is formed by the downstream part of the housing 11.

Part of the air compressed by the low pressure compressor 12 is delivered to this exhaust line via a bypass line 16, with the flowing through the bypass line 16 Compressed air bypasses the high pressure compressor 13, the incinerator 14 and the turbines 15.

The high pressure compressor 13 is a twelve-stage compressor with a cylindrical outer housing 20 (which e.g. device comprises consecutive, undivided drums) and a cylindrical inner housing 21 which is within the outer housing 20 is provided and attached to this 1st. The two housings 20, 21 are separated from one another by an annular space 22 separated, which for the purpose of pressure equalization (zJ3. by

/ nice

H28223

small holes (not shown) to the high pressure compressor 13 can be vented.

The inner housing 21 comprises four in the axial direction on top of one another following undivided hinge, 25,24,25,26 on the upstream Part of the high pressure compressor 13 and four axially successive split rings 27,28,29,30 am downstream (bearing of the high pressure compressor 13, soft the Divide space 22 into four unconnected chambers 22a, 22b, 22c, 22d. Each ring 23-30 has end flanges on both of its remote ones Ends, the end flanges of adjacent rings being connected to one another by screws 32

Each of the rings 23,24,25,26 and 30 carries a stage of stator blades 33 of the compressor, while each of the rings 27 »28 and 29 * carries two stages of such blades and with one Reinforcement ring 9 is equipped.

The undivided ring 23 at the upstream end of the high-pressure compressor 13 is attached by screw bolts 34 both to the outer housing 20 and to a number of struts 35 that are offset at an angle. Each of the rest of them. undivided rings 24.25 * 26 is like in Pig. 2, connected to the outer housing 20 only via its connection to the adjacent rings

The end flanges 36 at the upstream ends of the split rings 28,29,30 have edges 37 'which Ln stroxaabwärtiger.

909828/0366

Extend direction and engage in grooves 38 in the outer housing 20. Each end flange 36 has slots 40 (Figure 4) which extend to holes 41 and have the purpose of increasing its elasticity so that the split rings 27-30 of the shape of the outer housing 20 when starting the engine cold and b © when the engine is switched off hot.

The shiita © 40 in the flanges 36 at the upstream ends of the split rings 28, 29 and 30 are separated from the flanges 36a as the downstream ends of the split rings 2? b @ gw _e 28 or 29 covered in order to prevent the air from circulating again 3 ¥ iig © 3b.ea the chambers 22a ₉ 22b, 22c and 22d.

To di @ elasticity of the flanges 36a on the downstream.

lato dej? split ring © 27 ₉ 28,29, these are @n gwisch © n the places where they cut off the slots 40, as shown by the dashed ia Figure 4- "

Mg 8tat @ ^ gefeaiaf © I33. 35 cL®r two rings split on d @ m 28

a of the high-pressure compressor 13 have Plattfori © i ^ asela, hard solder or welding. together

Mm ¹ O © ia4 ₀ ϊεε @ © © isem f © II of the "split hinge 28" to form.

B; i © GiMQjMkXS © ®E! A @ Kbast © a Plattf © sm. @ N 45 siad shaped, 'dsiiSQj siöJä sms © li @ a Ito @ a Iaiftdui * cfeläss © s M- form, by tyel © ao eia Should aei? ia H © @ MS "ia © Isf © i? diefetci ^ 13 is © mprimiert © a Luft die-

A valve 45 controls the discharge of compressed air from the annular space 22 into the bypass line 16 and thus also that Venting compressed air through the air passages 44.

The remaining stator blades 33 (i.e. all except the upstream of the two from the split ring 28 seated Steps) have essentially elliptical platforms 46 (Pig.6), which by brazing or welding in accordingly shaped slots 47 of the respective rings 23-30 attached the radial thickness of the platforms 46 being substantially the same as the radial thickness of the corresponding ones Rings 23-30.

As can be seen in Figure 3, each split ring 27-30 is split along a line 48 which is substantially axial runs, but is also sinusoidal, so that it does not intersect any of the stator blades 33.

The compressor shown in the drawings was developed to prevent the fretting corrosion which it causes It can be that gas loads act on parts that can be moved relatively by these loads.

It can be seen that around with minimal rotor and stator tip clearances to be able to work, the rings 27-30 in the downstream, and therefore also the hottest part of the compressor 13 "are divided, and that these divided rings necessarily be held in position by parts 37 »38, which of such

909828/0366

Are particularly exposed to fretting corrosion. . ".:. - .. —- _______ ■■

The upstream, cooler part of the high-pressure compressor 13 can be seen with undivided rings 25-26_vexi , which are fastened in such a way that they are not exposed to such fretting corrosion.

The ^ platforms of stator blades are usually the btatorschaufeln and grooves come into grooves in the "compressor housing fes tgehsSiien, so it-sion phenomena Heibkoriio during operation to between platforms; these He will phenomena _T avoided by the one shown in the drawings construction.

Claims

Claims (1)

Pat e> quotes. ^/ 7l. ^N VerdicSbei ^ fTIF ^ tn gas turbine jet engine comprising a cylindrical outer casing and inner casing which is fixed within and attached to the outer casing, characterized in that -; axially successive rings (23-30) each carrying at least one step of stator blades (33), these rows of rings comprising a plurality of axially successive undivided rings (23-26), which at the upstream part of the compressor (13), and at least one ring (27-30) which is arranged on the downstream part of the compressor and is divided in a substantially axial direction, the or each divided ring having support means (36,37) that are directly connected to the outer housing (20) in such a way that they are supported on it * 2. Compressor according to claim 1, characterized in that at least one of the undivided rings (23-26) is connected to the outer housing (20) only via its connection to the adjacent rings. ¹ H28223 3. Compressor according to claim 1 or 2, characterized in that that on the downstream part of the compressor a plurality of axially successive divided Rings (27-30) is provided. 4 · Compressor according to one of the preceding claims, characterized characterized in that the split Hing, or at least one of the same, is provided with a flange (36) which the Forms support means and which is equipped with an edge (37) which engages in a groove (38) in the outer housing (20). 5. Compressor according to claim 4, characterized in that the or each flange (36) is preferably cut out in order to increase its elasticity so that these divided hinge de ^ formation adapt to the outer housing (20) 6. Compressor according to one of the preceding claims, characterized in that at least «ifcen @ one of the stages of the compressor consists of stator blades (33) with platforms (46) ″, which © dux? ch hard solder or smoldering in appropriately shaped® Slots (4?) Attached to the associated rings (23-30) ε lad * 7 «Compressor according to claim 6, characterized in that the radial © "Thickness of the platforms (46) in the 'we @@ atliehen the same is like the radial thickness of the accessory rings (23-30). 909828/0366 8. Compressor according to one of the preceding claims, characterized in that at least one of the stages consists of stator blades (33), which are provided with platforms (43) which are connected by brazing or welding in such a way that they form the Ging or part of it. 9 · Compressor according to claim 8, characterized in that they are connected to one another by hard solder or welding, next to one another lying platforms (43) are designed so that between them Luftausläese (44) are formed, through which a part of the air compressed in the compressor (13) can be discharged from this, whereby means are provided, to control the discharge of compressed air through these openings. 10. Compressor according to one of the preceding claims, characterized in that the compressor is a high pressure compressor (13) of a gas turbine jet engine and the engine is a bypass engine (10) which has a low-pressure regulator has denser (12), which releases part of the compressed air it has compressed through a bypass line (16). 11 · Compressor according to claim 8 and 10, characterized in that that the arrangement is made so that through the air outlet openings (44) air flowing through is released to the bypass line (16) © 909828/0366 -Al ' Blank page