Door seal for a turbomachine

Abstract

With a door seal for a gas turbine engine, a gap (3) existing between an axially symmetrical component (1) and an assembly formed by several segments (2) is sealed by seal doors (11), which are held via retaining holes (10) at retaining bolts (9) on one of the components, the seal doors (11) being pressed against sealing edges (5, 7) of the two components, with the sealing edges (5, 7) being disposed at a certain distance from each other. The retaining bolts and holes are located outside the pressure surface (A) of the seal doors, formed between the two sealing edges, thus preventing cooling air losses via a gap remaining between the retaining bolts and bores.

Description

This application claims priority to German Patent Application DE10 2006 017 377.5 filed Apr. 11, 2006, the entirety of which is incorporated by reference herein.

This invention relates to a door seal for a turbomachine, more particularly a gas turbine engine, used for sealing a gap existing between an axially symmetrical component and an assembly formed by several axially symmetrically arranged segments.

Door seals are, for example, used on gas turbine engines for sealing the axially symmetrically designed combustion chamber towards a stator vane row including a plurality of axially symmetrically arranged stator vane segments to separate areas of different pressure or different air systems, respectively. Door seals include a plurality of doors moveably held on a rivet whose side faces are lodged, or forced, against both a sealing edge formed by the axially symmetrical component and a sealing edge of the respective component segment by the overpressure existing on one side. Design or thermally incurred differences in the gap size between the axially symmetrical component and the respective component segment can thus be compensated.

Optimum sealing efficiency is obtained if, in the operating condition, the sealing edges on both sides are positioned such relative to each other that the door is in a vertical position. As this position can generally not be maintained on account of tolerances and thermal expansion, the doors will assume a canted attitude and their contact with the arc-shaped sealing edges of the axially symmetrical component and the component segments will pass from a linear to a punctiform state, giving rise to leakage. This disadvantage of the known door seals is counteracted in that the sealing edges are given a linear, not an arc-shaped course, i.e. they form a chord, not an arc. This type of sealing edge configuration, in which the doors tilt over straight edges, thus providing for safe sealing throughout the whole tolerance and displacement range, requires, however, increased radial installation space for the seal configuration.

Since the individual doors are tiltably retained, via retaining holes provided in the doors, at rivets or retaining bolts radially disposed between the two sealing edges, and the hole diameter required to ensure the tilting movement is larger than the bolt diameter, disadvantageous leakage losses occur via the gap between the bolt and the hole, i.e. pressure losses or cooling air losses, respectively, in the higher-pressure secondary air zone.

In a broad aspect the present invention provides a door seal with improved sealing efficiency for the reduction of cooling air leakage in an engine.

It is a particular object of the present invention to provide solution to the above problems by a door seal designed in accordance with the features described herein.

Useful embodiments of the present invention will be apparent from the description below.

In a gas turbine engine, the gap existing between an axially symmetrical component and an assembly formed by axially symmetrically arranged segments is sealed by means of several seal doors which are tiltably held via retaining holes at retaining bolts and which separate zones of different pressure and, under the effect of a pressure force, lodge against sealing edges disposed at a certain distance from each other. In accordance with the present invention, the distance between the sealing edges is reduced and the retaining bolts and holes are located in an area outside the now smaller pressure surface. Cooling air is prevented from transgressing into the lower-pressure zone via the gap which is required between the retaining bolt and the retaining hole to enable the tilting movement to be performed, thus providing a robust secondary air system by way of a reduction of the cooling air losses.

The sealing edges are provided on first and second fins of the component and the segments of the component assembly. The retaining bolts are attached to one of the fins, with the fin provided for attachment being radially extended towards the other fin, thus reducing the distance between the sealing edges and, ultimately, the pressure surface onto which pressure is applied to force the seal door into the sealing position.

In the axially symmetrical system, the sealing edges feature a preferably straight course to further enhance sealing efficiency.

An example of the present invention is more fully described in the light of the accompanying drawing.

FIG. 1 shows a longitudinal sectional view of a door seal between an axially symmetrical component, e.g. a combustion chamber, and an assembly formed by individual axially symmetrically arranged segments, in this case, a stator vane row for a gas turbine engine consisting of individual stator vane segments.

The gap 3 existing between the axially symmetrical component 1 and the appertaining—axially symmetrically arranged—segments 2 is sealed by a segmented door seal. The free face of a circumferential first fin 4 formed onto the axially symmetrical component 1 provides a circumferential first sealing edge 5. On a second fin 6 projecting from each segment 2 towards the circumferential fin 4, a second sealing edge 7 is provided at the upper end. Attached in the lower portion of the second fin 6 and in a locating fin 8 arranged at a certain distance from the second fin 6 is a retaining bolt 9 at which a seal door 11 is tiltably held via a retaining hole 10. The seal door 11 seals a zone of higher pressure P1 against a zone of lower pressure P2 to avoid cooling air losses.

The diameter of the retaining hole 10 is larger than that of the retaining bolt 9 in order to enable the seal door 11 to be tilted, thereby compensating changes and differences in the gap width caused by tolerances and thermal expansion and ultimately improving sealing efficiency. The side face of the seal door 11 lodges on the first sealing edge 5 in the upper area and on the second sealing edge 7 in the center area. The second sealing edge 7—being arranged in the center area of the seal door 11 and above the retaining hole 10—prevents transgression of cooling air from the zone of higher pressure P1 via the retaining hole 10 into the zone of lower pressure P2. It was found that the pressure force F1 acting upon the reduced pressure surface A between the two sealing edges 5 and 7 or the difference between the pressure forces F1 and F2 acting on both sides of the seal door 11, respectively, is still sufficient to ensure sealing at the sealing edges 5 and 7 preferably designed as straight lines.

LIST OF REFERENCE NUMERALS

• 1 Axially symmetrical component
• 2 Segments
• 3 Gap
• 4 First (circumferential) fin of 1
• 5 First sealing edge of 4
• 6 Second fin of 2
• 7 Second sealing edge of 6
• 8 Locating fin of 2
• 9 Retaining bolt
• 10 Retaining hole of 11
• 11 Seal door
• P1 Zone of higher pressure
• P2 Zone of lower pressure
• A Pressure surface of 11, between 5 and 7
• F1, F2 Pressure forces acting on A

Claims

1. A door seal for a turbomachine, for sealing a gap between an axially symmetrical first component and a second component formed by several axially symmetrically arranged segments comprising: a first sealing edge on the first component; a second sealing edge on the second component; a plurality of seal doors; a plurality of retaining bolts positioned in respective retaining holes on one of the components; the seal doors being tiltably held on the retaining bolts to simultaneously engage the first and second sealing edges of the two components and separate zones of different pressure, with the sealing edges being disposed at a certain distance from each other, and which are subjected to a sealing pressure force F1 acting upon a pressure area A between the two sealing edges, the retaining bolts and retaining holes being arranged outside the pressure area A, with the size of the pressure area A being sufficient for achieving the pressure force F1 sufficient to maintain the seal doors sealed against the sealing edges during operation of the turbomachine.

2. A door seal in accordance with claim 1, wherein the first and second sealing edges are formed on first and second fins respectively of the first and second components, with the retaining bolts being attached at one of the fins and the where the fin provided for such attachment extends toward the other fin.

3. A door seal in accordance with claim 2, and further comprising a third fin for additionally attaching the retaining bolts such that each retaining bolt is held by two fins.

4. A door seal in accordance with claim 3, wherein the sealing edges are in the form of at least one of circular arcs and chords.

5. A door seal in accordance with claim 2, wherein the sealing edges are in the form of at least one of circular arcs and chords.

6. A door seal in accordance with claim 1, wherein the sealing edges are in the form of at least one of circular arcs and chords.