Patent Application
20120328996
The disclosure relates to gas turbine engines. More particularly, the disclosure relates to attaching ceramic matrix composite (CMC) ducts in reverse flow combustors.
Ceramic matrix composite (CMC) materials have been proposed for various uses in high temperature regions of gas turbine engines. US Pregrant Publication 2010/0257864 of Prociw et al. (the disclosure of which is incorporated herein in its entirety as if set forth at length) discloses use in duct portions of an annular reverse flow combustor. The annular reverse flow combustor turns the flow by approximately 180 degrees from an upstream portion of the combustor to the inlet of the turbine section. Viewed in axial/radial section, an inlet dome exists at the upstream end of the combustor. Additionally, an outboard portion of the turn is formed by a large exit duct (LED) and an inboard portion of the turn is formed by a small exit duct (SED). The LED and SED may be formed of CMC. The CMC may be secured to adjacent metallic support structure (e.g., engine case structure). The SED and LED are alternatively referred to via the same acronyms but different names with various combinations of “short” replacing “small”, “long” replacing “large”, and “entry” replacing “exit” (this last change representing the point of view of the turbine rather than the point of view of the upstream portion of the combustor). An outer air inlet ring is positioned between the LED and the OD of the inlet dome. An inner air inlet ring is positioned between the SED and the ID of the inlet dome.
Robustly and efficiently attaching a CMC to the metal presents engineering challenges.
One aspect of the disclosure involves a reverse flow combustor having an inlet end. A flowpath extends downstream from the inlet end through a turn. The turn directs the flowpath radially inward and reversing an axial flow direction. A large exit duct (LED) is along the turn. A small exit duct (SED) is along the turn and joined by a joint to a mounting structure to resist separation in a first axial direction. The joint comprises: a first surface on the SED facing partially radially inward; and a mounting feature engaging the first surface.
In various implementations, the SED may comprise a thickened upstream region. The first surface may be a shoulder formed by the thickened upstream region.
The details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims.
Like reference numbers and designations in the various drawings indicate like elements.
The terms axial and radial as used herein are intended to be defined relative to the main central longitudinally extending engine axis 11 (centerline). Further, when referring to the combustor 16 herein, the terms upstream and downstream and intended to be defined relative to the general flow of air and hot combustion gases in the combustor, i.e. from a fuel nozzle end of the combustor where fuel and air are injected for ignition to a combustor exit where the combustion gases exit toward the downstream first turbine stage.
Referring to
The inner liner 17 extends from an upstream end 21 of the combustor 16 (where a plurality of fuel nozzles 30, which communicate with the combustion chamber 23 to inject fuel therein, are located) to a downstream end (relative to gas flow in the combustion chamber) defining the combustor exit 27. The inner liner 17 is, in at least one embodiment, comprised of the main liner portions, namely a dome portion (inlet dome) 24 at the upstream end (inlet end) 21 of the combustor, and a long exit duct portion 26 and a short exit duct portion 28 which together form the combustor exit 27 at their respective downstream ends. Each of the dome portion 24, long exit duct portion 26 and short exit duct portion 28, that are made of the CMC material and which make up a substantial part of the inner liner 17, have a substantially hemi-toroidal shape and constitute an independently formed shell.
Although ceramic materials have excellent high temperature strength, their coefficients of thermal expansion (CTE) are much lower than those of metals such as the rings 32 and 34. Thermal stress arising from the mismatch of CTEs poses a challenge to the insertion of CMC combustor liner components into gas turbine engines. Exemplary joints thus allow relative movement between the CMC and its metal support structure(s), without introducing damaging thermal stresses.
The nature of the dome 24 and the LED 26 make them relatively easy to compliantly mount. In axial/radial section their exterior surfaces (away from the hot gas of the combustor interior) are generally convex. It is thus easy to compliantly compressively hold them in place. For example, the exemplary dome and LED are contained within respective shells 40 and 50 with compliant mounting members 42 and 52 respectively engaging the exterior surfaces 44 and 54 of the dome and SED. The exemplary shells 40 and 50 are metallic shells mounted to adjacent structure. The exemplary spring members 42 are half leaf spring tabs secured to the interior surface of the shell 40. The exemplary spring members 52 are more complex assemblies of pistons and coil springs with piston heads engaging the LED exterior surface 54.
The exemplary dome further includes an interior surface 45, an outboard rim 46, and an inboard rim 47. The exemplary liner section 40 also includes an outboard rim 48 and an inboard rim 49. The exemplary outboard rim 48 is secured to a mating surface of the outer air inlet ring (outer ring) 34 (e.g., via welding) and the exemplary inboard rim 49 is secured to the inner air inlet ring (inner ring) 32 such as via welding.
Similarly, the LED has an interior surface 53, upstream rim 55 and a downstream rim 56. The liner 50 includes an upstream portion (e.g., a rim) 57 and a downstream portion (e.g., a flange) 58. The exemplary rim 57 is secured to the outer ring 34 (e.g., via welding). The exemplary flange 58 is secured to a corresponding flange 60 of the platform ring (inner ring) 61 of an exit vane ring 62. The exemplary exit vane ring 62 includes a circumferential array of airfoils 63 extending from the platform 61 to a shroud ring (outer ring) 64.
The SED extends from an upstream rim 80 to a downstream rim 82 and has a generally convex interior surface 84 and a generally concave exterior surface 86. The LED downstream rim 56 and SED downstream rim 82 are proximate respective upstream rims 88 and 90 of the vane inner ring 61 and outer ring 64. The first blade stage of the first turbine section is downstream of the vane ring 62 with the blade airfoils 66 shown extending radially outward from a disk 68.
For mounting of the SED, a leading/upstream portion/region 100 of the SED is shown directed radially inwardly toward the upstream rim 80 (e.g., off-axial by an angle θ1). The exemplary SED is of generally constant thickness (e.g., subject to variations in local thickness associated with the imposed curvature of the cross-section of the SED in the vicinity of up to 20%). The inward direction of this portion 100 thus creates associated approximately frustoconical surface portions 102 and 104 of the surfaces 84 and 86 along the region 100. The surface portion 104 thus faces partially radially inward. The surface portion 104 may, thus, be engaged by an associated mounting feature to resist axial separation in a first axial direction 106 (forward in the exemplary engine wherein combustor inlet flow is generally forward). Movement in a second direction 107 opposite 106 is resisted by engagement of the surface portion 102 with a corresponding angled downstream surface 108 of the ring 32 (e.g., also at θ1). Exemplary θ1 are 20-60°, more narrowly, 30-50° or 35-45′). The SED may be retained against outward radial movement/displacement by engagement of the surface portion 102 with the downstream surface 108 and/or by hoop stress in the CMC. For example, alternative implementations may lack the surface 108 and thus rely entirely upon hoop stress to retain the SED against outward radial movement. An exemplary SED is formed of CMCs such as silicon carbide reinforced silicon carbide (SiC/SiC) or silicon (Si) melt infiltrated SiC/SiC (MI SiC/SiC). The CMC may be a substrate atop which there are one or more protective coating layers or adhered/secured to which there are additional structures. It may be formed with a sock weave fiber reinforcement including continuous hoop fibers.
The exemplary mounting feature comprises a circumferential array of radially outwardly-projecting distal tabs 110 of a metallic clamp ring 112. The clamp ring is pulled axially in the direction 107 via an annular array of hook bolt assemblies 114. Exemplary hook bolt assemblies 114 are mounted to the dome shell 40. Exemplary hook bolt assemblies include a fixed base (support) 120 mounted to an inboard portion of the dome shell. A threaded shaft 122 extends through an aperture in the base 120 and is engaged by a nut 124 which may be turned (tightened) to draw the shaft at least partially axially in the direction 107. The shaft is coupled to a hook 126 (see also,
In the exemplary mounting configuration, the gripping of the portion 100 is the only mounting of the SED with the downstream rim 82 being slightly spaced apart from adjacent structures.
Rotational registration and retention of the SED to the ring 32 may also be provided. Exemplary rotational registration and retention means comprises a circumferential series of recesses 140 (
The SED 301 may be installed by a process comprising: 1) sliding the U seal 312 onto the metal baffle plate 316; 2) cooling the assembly of the seal 312 and plate 316 to thermally contract them (e.g., to −40 C); 3) heating the CMC SED 301 to expand it (e.g., to 1000 C); 4) sliding/inserting the cooled assembly of seal 312 and plate 316 into the heated CMC SED 301; and 5) welding the baffle plate 316 to inner air inlet ring 306. Thus, during the inserting, the SED is at a hotter-than-ambient temperature and the assembly is at a cooler-than-ambient temperature
One or more embodiments have been described. Nevertheless, it will be understood that various modifications may be made. For example, when implemented in the remanufacture of the baseline engine or the reengineering of a baseline engine configuration, details of the baseline configuration may influence details of any particular implementation. Accordingly, other embodiments are within the scope of the following claims.
