EP2543826A2

EP2543826A2 - Composite shroud

Info

Publication number: EP2543826A2
Application number: EP12174977A
Authority: EP
Inventors: Paul F. Croteau; Kevin E. Green; Jun Shi
Original assignee: United Technologies Corp
Current assignee: RTX Corp
Priority date: 2011-07-05
Filing date: 2012-07-04
Publication date: 2013-01-09
Also published as: EP2543826A3; US20130011248A1

Abstract

A shroud (18) for use in a gas turbine engine (10) has a ring with a plurality of protrusions (30) and a plurality of slots (34), each of the protrusions (30) having an arc length (A2) and parallel sides (32).

Description

BACKGROUND

The present disclosure is directed to a geometry to minimize feature related thermal stresses in a monolithic ceramic or Ceramic Matrix Composite (CMC) shroud used in a gas turbine engine.
The incorporation of a ceramic or CMC shroud in the hot section of a gas turbine engine as a replacement of a similar metallic component is beneficial. A metal shroud requires substantial cooling in order to withstand the high temperature in the turbine section. Often a metal shroud is composed of multiple arc sections held by a complex assembly of support hardware to provide close positional tolerance and circularity to provide gap control with the rotor blade tips. A one piece ceramic shroud, by virtue of its inherent thermal material properties and high temperature capability, provides the ability to reduce the running blade tip clearance and reduced cooling air, providing improvements in efficiency and increased power.
From a thermal stress point of view, a simple ring structure provides the most stable structure with the least distortion and lowest thermal stress. Various techniques exist for shroud support which require designing and fabricating the shroud ring structure with features onto which to support and locate the shroud within the metal assembly. Features may range from tabs or protrusions on the outer diameter surface or on one or both end faces, to slots or grooves on the outer diameter surface of the shroud. Although consideration needs to be made for attachment and assembly of the ceramic shroud, structural considerations also need to be made to insure ceramic integrity and life.

SUMMARY

In accordance with the present disclosure, there is provided a shroud comprising a ring with a plurality of protrusions and a plurality of slots and each of said protrusions having an arc length and parallel sides.
Further in accordance with the present invention, there is provided an engine broadly comprising a rotor and ceramic shroud surrounding said rotor and said shroud comprising a ring with a plurality of protrusions and a plurality of slots and each of said protrusions having an arc length and parallel sides.
Other details of the monolithic ceramic or CMC shroud having reduced thermal stresses are set forth in the following detailed description and the accompanying drawings in which like reference numerals depict like elements.

BRIEF DESCRIPTION OF THE DRAWINGS

Fig. 1 is a sectional view of a gas turbine engine;
Fig. 2 is a perspective view of a shroud in accordance with the present disclosure;
Fig. 3 is a side view of a portion of the shroud of Fig. 1;
Fig. 4 is a sectional view of a metal ring mating with the shroud of Fig. 2; and
Fig. 5 is a graph showing stress relative to slot arc length for a thermally stressed shroud ring.

DETAILED DESCRIPTION

There is shown in Fig. 1, a cross section of an engine 10. The engine includes a compressor 12 through which a fluid flows and is compressed, a combustor 14 in which the compressed fluid is mixed with a fuel and combusted, and a turbine section 24 in which the heated fluid is expanded to drive the turbine for creating power to drive the compressor 12 and other systems. As can be seen in Figs. 1 and 2, the turbine section 24 includes a turbine vane 16, a turbine shroud 18, a turbine rotor 20, and a turbine support case 22.
From a thermal stress point of view, the ideal structure would be a simple ring structure. This is because such a structure provides the most stable structure with the least distortion and lowest thermal stress. For purposes of holding and positioning the shroud in the engine assembly, the ring structure of shroud 18 as shown in Fig. 2 may have a plurality of outer diameter protrusions 30 creating slots 34 with parallel sides 32. The use of parallel sides 32 across slot 34 is useful and relevant when the arc length of slot A1 is much less than arc length of A2. For embodiments of the shroud where A2<<A1, it is useful and relevant for sides 32 to be parallel across protrusion 30.
A simple ring provides the hoop strength and the stable structure needed to withstand the thermal gradient that the shroud 18 will be exposed to. A ring structure with uniform thickness and no other features, such as tabs or slots, exposed to a uniform through thickness temperature gradient, can exhibit stresses considered acceptable for ceramics used for this purpose. The loading experienced in the ring structure from a through thickness temperature gradient is a bending load, with the hotter inner diameter surface in compression and the cooler outer diameter surface in tension. If the ring were unwrapped into a simply supported flat bar, the temperature gradient would cause a differential of thermal expansion from one side to the other and cause the bar to bend. To eliminate the deformation from the flat bar, a pure moment, equal and opposite, would need to be applied at each end of the bar. But if the bar is shaped into a hoop and the ends joined to form a ring with uniform cross section, the bending loading at each end of this joint is equal and opposite, and therefore prevents any deformation due to bending. The only deformation of the ring is thermal expansion typical of any heated volume of material.
A featureless ring, though, is not practical and some means are needed to provide support and location of the ring structure to the assembly. Various features pertaining to assembly have been proposed and may be valid for reasons specific to the design requirements. But once a feature is introduced into the structure of the ring and eliminates the constant cross section of the ring, the bending load in the ring becomes evident through higher strains and ring distortion. Depending on the feature, the distortion and localized high strain can cause increased stress and stress concentrations. These stress concentrations are most often associated with fillets at the attachment feature and are inherently tensile surface stresses or 1st principal stresses.
As can be seen from Figs. 2 and 3, the shroud 18 is provided with a plurality of slots 34 bordered by the sides 32 of adjacent protrusions 30. Each slot 34 has an inner surface 36 which may be either a flat surface of a curved surface with a radius R1. Further, each slot 34 has a slot arc length A1. As noted before, each protrusion 30 has an arc length A2. The slots 34 may be equally spaced around the periphery of the shroud 18. There may be from 3 to 18 slots 34. Each slot 34 may have an arc length in the range of 20 to 60 degrees.
As noted before, the sides 32 of the slots 34 are parallel. With a multitude of identical slots positioned around the circumference of the ring 38 forming the shroud 18, concentric and circumferential position of the ring 38 can be maintained with a mating ring 40 with mating features 42 that contact the parallel sides 32 of each slot as shown in Fig. 5. The parallel sides 32 of each slot 34 allows thermal expansion of the ring 38 relative to its support ring 40 with introducing additional stress due to thermal mismatch between mating parts.
With slot arc lengths much less than protrusion arc lengths, or A1 << A2, than a majority of the ring 38 is dominated by the maximum ring thickness T2. This provides a stiffer cross section to withstand the bending load from the through thickness thermal gradient. This may cause a significant stress riser in the fillet region 33 of the slots 34 where the stress increases with decreasing slot arc length.
Conversely, as the arc length A2 of the protrusion 30 decreases and the arc length A1 of the slot 34 increases, then a majority of the ring 38 is dominated by the minimum ring thickness T1 and the stress concentrations decreases. The mounting feature becomes the parallel sides 32 of a protrusion feature 30 for when A1 >> A2.
Fig. 5 shows the relationship of stress concentrations for a shroud ring 38 with varying arc lengths of protrusions 30 and slots 34, where the stress is normalized relative to the maximum stress condition for a 5 slot ring. A thermal finite element model was solved for a given temperature gradient through the thickness of the ring. The thermal solution was then passed to a structural finite element model to solve for the thermally induced stresses. Curve 1 is for a ring with five slots and protrusions. It indicates that the stress concentration in the fillet region decreases significantly as the slot arc length increases, to about 1/3 of the maximum stress of that of the narrowest slot. Note that there appears to be an optimal protrusion arc length of approximately 20 degrees, or a slot arc length of 52 degrees, as illustrated by Curve 1 for the five slot/protrusion ring, where the stress concentration is at 27% of the maximum case.
Curve 2 in Fig. 5 is for a similar shroud ring with 12 slots and protrusions with similarly changing arc lengths. Note that the magnitude of the stress concentration is essentially equal for when arc lengths of the slots are at the maximum, or where the arc lengths of the protrusions are equal. Also, the maximum stress for when the slot is at its minimum is lower for the 12 slot ring as compared to the 5 slot ring, which is expected as 12 slots allow more deflection of the ring from the internal bending load induced from the through thickness temperature gradient. It is interesting to note that the same optimal protrusion arc length for the 5 slot case is not apparent for the 12 slot/protrusion case shown in Curve 2.
The maximum hoop stress of a plain ring thickness T1 is approximately 15% less than the lowest maximum stress condition, as shown by the dotted line 3 in Fig. 5.
A featureless shroud ring is not a useful solution for assembly into the hot section of a gas turbine engine. Therefore, the geometry that provides the least thermally induced stress is a ring with a multitude of protrusions with an arc length as small as practical to provide adequate mounting support. From Fig. 5, it is apparent that more slots for a given slot length will reduce the maximum stress. Also, Fig. 5 shows that as the slot length increases, the maximum stress decreases, indicating that protrusions are more desirable than slots, from a stress point of view.
While there has been discussed herein, a shroud 18 having 5 to 12 slots, determining the number of useful slots to use in a particular design application depends on issues including manufacturing cost. It follows that the more features the ring will have will in turn increase the cost of the shroud ring. Close tolerance control in ceramic components requires much of the machining of the contact surfaces and other critical features need to be done in the ceramic's hardened state. Therefore, to decrease manufacturing costs, as much machining in the green state should be performed prior to densification if the ceramic, leaving only a minimal amount of machining to obtain the required tolerance.
The shroud ring 18 may be formed from any suitable ceramic material known in the art. The shroud ring 18 may be a monolithic ceramic material.
There has been discussed herein a geometry to minimize feature related thermal stresses in a monolithic ceramic shroud. While the geometry has been described in the context of specific embodiments thereof, other unforeseen alternatives, modifications, and variations may become apparent to those skilled in the art having read the foregoing description. Accordingly, it is intended to embrace those alternatives, modifications, and variations, as fall within the broad scope of the appended claims.

Claims

A shroud (18) comprising:
a ring with a plurality of protrusions (30) and a plurality of slots (34), each of said protrusions (30) having an arc length (A2) different from the arc length (A1) of each said slot (34).
The shroud (18) of claim 1, wherein said shroud (18) is formed from a monolithic ceramic material or Ceramic Matrix Composite (CMC) material.
An engine (10) comprising:
a rotor (20);

a ceramic or CMC shroud (18) surrounding said rotor (20), said shroud (18) comprising a ring with a plurality of protrusions (30) and a plurality of slots (34), each of said protrusions (30) having an arc length (A1) and parallel sides (32).
The engine (10) of claim 3, wherein said shroud (18) is located in a hot section (24) of said engine (10).
The engine (10) of claim 3 or 4, wherein said shroud (18) is formed from a ceramic material and is monolithic.
The shroud (18) or engine (10) of any preceding claim, wherein each of said slots (34) has parallel sides (32).
The shroud (18) or engine (10) of claim 6, further comprising a metal ring (40) with mating features (42) that contact the parallel sides (32) of the slots (34).
The shroud (18) or engine (10) of any preceding claim, wherein said slots (34) are equally spaced around a circumference of said ring.
The shroud (18) or engine (10) of any preceding claim, wherein said plurality of slots (34) comprises said ring having from 3 to 18 slots or optionally from 5 to 12 slots (34).
The shroud (18) or engine (10) of any preceding claim, wherein each said slot (34) has an arc length (A2) and said arc length (A2) of each slot (34) is greater than the arc length (A1) of each said protrusion (30).
The shroud (18) or engine (10) of any preceding claim, wherein said ring has a minimum thickness (T1) and a majority of the ring is dominated by the ring minimum thickness (T1) so as to decrease stress concentrations.
The shroud (18) or engine (10) of any preceding claim, wherein each said slot (34) has an arc length (A1) in the range of 20 to 60 degrees.
The shroud (18) or engine (10) of any of claims 1 to 11, wherein each said slot (34) has an arc length (A1) in the range of 3 to 20 degrees.