Housing section of a turbine engine compressor stage or turbine engine turbine stage

Abstract

A housing section of a turbine engine compressor stage or a turbine engine turbine stage that, in particular, has a closed and annular-shaped, radially outer casing. The radially outer casing has radially inwardly extending webs that are angled at a slant relative to the radius.

Claims

1. A housing section of a turbine engine compressor stage or turbine engine turbine stage comprising: a closed and annular-shaped, radially outer casing; an inner casing located radially inward of the outer housing casing and separated from the outer housing casing, the inner housing casing located radially outward from a plurality of rotor blades of the turbine engine compressor stage or turbine engine turbine stage; wherein the outer housing casing has a radius having radially inwardly extending webs, the webs being angled at a slant relative to the radius, each web having a first end and a second end, each web being joined to a surface of the inner housing casing at the first end and joined to a surface of the outer housing casing at the second end.

2. The housing section as recited in claim 1 wherein the webs are axially or circumferentially angled at a slant relative to the radius; wherein the webs define at least one hollow space and wherein the at least one of the hollow spaces defined by the webs communicate with a coolant inlet or coolant outlet.

3. The housing section as recited in claim 1 wherein, in a cross section, the webs form a grid or a honeycomb structure.

4. The housing section as recited in claim 1 wherein the webs are prefolded numerous times.

5. The housing section as recited in claim 1, wherein the housing section includes a stiffening structure configured in a hollow space between the webs.

6. A turbine engine comprising at least one housing section as recited in claim 1.

7. A gas turbine comprising the turbine engine as recited in claim 1.

8. The housing section as recited in claim 1, further comprising an abradable coating on a side of the inner housing casing opposite the webs.

9. A housing section of a turbine engine compressor stage or turbine engine turbine stage comprising: a closed and annular-shaped, radially outer casing; an inner casing located radially inward of the outer housing casing and separated from the outer housing casing, the inner housing casing located radially outward from a plurality of rotor blades of the turbine engine compressor stage or turbine engine turbine stage; wherein the outer housing casing has a radius having radially inwardly extending webs, the webs being angled at a slant relative to the radius, each web having a first end and a second end, each web being joined to a surface of the inner housing casing at the first end and joined to a surface of the outer housing casing at the second end; wherein the webs are prefolded in a radial direction.

10. The housing section as recited in claim 7 wherein the webs define at least one hollow space.

11. The housing section as recited in claim 10 wherein the web surround the at least one hollow space.

12. The housing section as recited in claim 10 wherein at least one of the hollow spaces defined by the webs communicates with a coolant inlet or coolant outlet.

13. The housing section as recited in claim 9 wherein the webs are prefolded in a zigzag shape, convexly or concavely.

14. The housing section as recited in claim 13 wherein the stiffening structure has a grid or honeycomb structure in cross section.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Further features and advantages will become apparent from the dependent claims and the exemplary embodiment. In this regard:

(2) FIG. 1 shows a longitudinal section of a housing section in accordance with one embodiment of the present invention;

(3) FIG. 2 shows a longitudinal section of a housing section in accordance with a further embodiment of the present invention;

(4) FIG. 3 shows a longitudinal section of a housing section in accordance with a further embodiment of the present invention, including an inner casing and separate abradable means, such as abradable or run-in coating;

(5) FIG. 4 shows a longitudinal section of a housing section in accordance with a further embodiment of the present invention, without an inner casing and with integrated abradable means.

DETAILED DESCRIPTION

(6) In the following, similarly designed components of the particular variants are provided with the same reference numerals and are denoted the same way.

(7) In accordance with a first variant, housing section 1 shown in FIG. 1 has a radially outer casing 10 and an inner casing 11. Radially outer casing 10 is separated from inner casing 11 by a hollow space 13. In hollow space 13, a plurality of webs 12 extend radially inwardly from radially outer casing 10. At one end, webs 12 are joined to radially outer casing 10 and, at the other end, to inner casing 11. A flow channel casing 16, which defines a flow space 2, is configured radially inwardly from inner casing 11. Rotor blades 4 (shown in FIGS. 2 and 4 discussed below) are configured in flow space 2. Also illustrated in dashed lines is an optional stiffening portion 17 of the housing between the webs 12.

(8) In addition, housing section 1 features a plurality of mutually axially offset guides 14 for adjustable guide vanes (not shown in FIG. 1). Guides 14 are each integrally formed with radially outer casing 10 and inner casing 11, and are joined by form-locking, a substance-to-substance bond and/or frictionally to flow channel casing 16.

(9) Webs 12 are prefolded numerous times and thus angled at a slant relative to the radius, so that, in the event housing section 1 is subject to a load application, webs 12 are folded in accordance with a predefined folding characteristic. In particular, a radial folding of webs 12 takes place. Webs 12 are disposed axially mutually adjacently within hollow space 13 and prefolded numerous times in a zigzag shape.

(10) A longitudinal section of a housing section 100 in accordance with a further embodiment of the present invention is shown in FIG. 2. Housing section 100 features a radially outer casing 10 from where a plurality of webs 129 extend radially inwardly, webs 120 being interconnected. Webs 120 are axially slanted; in the illustrated case, webs 120 extending diagonally to a longitudinal axis (not shown) of housing section 100 (horizontally in FIG. 2).

(11) In a cross section orthogonally to the longitudinal web axis, interconnected webs 120 form a grid or honeycomb structure.

(12) In addition to housing section 100 shown in FIG. 2, housing section 100 illustrated in FIG. 3 features an inner casing 11. Webs 120 are joined to radially outer casing 10. Analogously to webs 120 illustrated in FIG. 2, webs 120 shown in FIG. 3 surround hollow spaces, through which cooling air from a cooling air inlet (left in FIG. 3) is directed to a cooling air outlet (right in FIG. 3), as indicated in FIG. 3 by flow arrows.

(13) At the side of inner casing 11 facing away from webs 120, a radially inwardly extending abradable means 3 is provided. Abradable means 3 may come in contact with a rotor blade 4 and is used, in particular, for reducing an undesired leakage flow between rotor blade 4 and inner casing 11 of housing section 100.

(14) At the upstream side thereof (left in FIG. 3), housing section 100 is joined in connecting portion 14 via a screw connection to a housing shell 200. In addition, at the downstream side thereof (right in FIG. 3), housing section 100 is joined via another connecting portion 14 to another housing shell 201. Each of the two housing shells 200, 201 may surround a guide vane stage (not shown). The connection of further housing shell 201 with housing section 100 may be a form-locking connection.

(15) Housing section 100′ illustrated in FIG. 4 differs from housing section 100 shown in FIG. 3 in that no inner casing 10 is provided therein. Abradable means 3′ is formed in one piece with webs 120′. It is ensured in this context that the abradable means is positioned in a way that allows it to come in contact with rotor blades 4′.

(16) Webs 120, 120′ illustrated in FIG. 2 through 4 are formed and oriented in a way that allows at least one portion of the hollow spaces surrounded in each case by the webs to communicate with a cooling air inlet port and/or a cooling air outlet port. The cooling air inlet port is provided in connecting portion 14, and the cooling air outlet port in further connecting portion 15. The cooling air inlet port and the cooling air outlet port communicate with a cooling air channel provided in respective housing shell 200, 201.

(17) Thus, the formation and orientation of the webs may ensure that cooling air flows via the cooling air inlet port into the hollow spaces of the webs and via the same to the cooling air outlet port. As a result, cooling air is able to flow via housing section 100 between two housing shells 200, 201 that are adjacently disposed in the longitudinal axis direction of the turbine engine, arrows P illustrating the direction of flow of the cooling air in the figures. The webs and the cooling air inlet port and the cooling air outlet port are configured in a way that does not allow the cooling air to communicate with flow space 2 of the turbine engine.

LIST OF REFERENCE NUMERALS

(18) 1 housing section in accordance with the first variant

(19) 2 flow space

(20) 3 abradable means

(21) 4 rotor blade

(22) 10 radially outer casing

(23) 11 inner casing

(24) 12 web in accordance with the first variant

(25) 13 hollow space

(26) 14 connecting portion

(27) 15 further connecting portion

(28) 16 flow channel casing

(29) 100 housing section in accordance with the second variant

(30) 100′ housing section in accordance with the third variant

(31) 120 web in accordance with the second variant

(32) 200 housing shell

(33) 201 further housing shell

(34) P flow direction of the cooling air