Patent Application
20250075632
The present disclosure relates generally to containment of gas turbine engine bladed rotors, and more particularly, to containment cases with additional features located within the containment section.
Gas turbine engines require containment of blades and rotor components following catastrophic failure. Some containment cases include attachments points or other features protruding inward or outward from the casing. When additional features are located within the containment section of the casing, the thickness of the casing is increased to counteract rupture of the casing following a blade or rotor segment impact in the vicinity of the feature. Further, casings with local features within the containment zone may have increased containment thickness and weight for a given design impact energy relative to analogous casing without local features. Increased weight of the gas turbine engine decreases engine efficiency.
A containment case, according to an example embodiment of this disclosure, includes an annular body bound by an outer surface and an inner surface, and an outer surface feature extending outward from the outer surface. The annular body includes a containment section and a reinforcement section. The containment section has a casing thickness defined by a radial distance between the inner surface and the outer surface. The reinforcement section subtends a sector of the containment section that defines a reinforcement thickness between the inner surface and the outer surface that is greater than the casing thickness. The outer surface feature at least partially may coincide with the reinforcement section.
A gas turbine engine, according to another example embodiment of this disclosure, includes a blade rotor and a containment case. The bladed rotor is operatively associated with the direction of rotation about an axis of the gas turbine engine. The containment case includes an annular body and an outer surface feature. The annular body is bound by an outer surface and an inner surface. The outer surface feature extends outward from the outer surface. The annular body includes a containment section and a reinforcement section. The containment section has a casing thickness defined by a radial distance between the inner surface and the outer surface. The reinforcement section subtends a sector of the containment section that defines a reinforcement thickness between the inner surface and the outer surface that is greater than the casing thickness. The outer surface feature at least partially coincides with the reinforcement section, which circumferentially precedes the outer surface feature relative to the direction of rotation.
As depicted in
Gas turbine engine 10 includes propeller 22, reduction gearbox 24, input shaft 26, and output shaft 28 for propelling an aircraft. Energy extracted by turbine section 18 drives input shaft 26, which is connected to an input of reduction gearbox 24. Reduction gearbox 24 drives output shaft 28 at a reduced speed proportional to a rotational speed of input shaft 26. Propeller 22 is rotationally coupled to output shaft 28, which drives propeller 22 during operation of gas turbine engine 10.
Compressor section 14 and turbine section 18 each includes one or more stages, each stage including at least one row of circumferentially spaced stationary vanes paired with at least one row of circumferentially spaced rotor blades. Compressor section 14 and turbine section 18 can include multiple compressor sections 14 and/or multiple turbine sections 18, each compressor section 14 connected to at least one corresponding turbine section 18 via a shaft. For instance, gas turbine engine 10 can include a low-pressure compressor, a high-pressure compressor, a high-pressure turbine, and a low-pressure turbine. The high-pressure compressor, high-pressure turbine, and high-pressure shaft form a high-pressure spool and the low-pressure compressor, low-pressure turbine, and low-pressure shaft form a low-pressure spool. The high-pressure spool is arranged concentrically with low-pressure spool. In such examples, air entering air inlet 12 flows through, in series communication, the low-pressure compressor and the high-pressure compressor of compressor section 14, combustor 16, the high-pressure and low-pressure turbines of turbine section 18 before discharging from exhaust section 20. In other examples, turbine section 18 can include a power turbine or free turbine which is not rotationally coupled to a compressor section 14 but is rotationally coupled to a propulsor such as propeller 22.
In each of the foregoing configurations, and other variants thereof, gas turbine engine 10 can include one or more containment cases 30 disposed about respective bladed rotors 32 of compressor section 14 and/or turbine section 18. Containment case 30 can be configured to enclose a single bladed rotor 32, or multiple axially adjacent bladed rotors 32. In each instance, containment case 30 or cases 30 can support stationary components of gas turbine engine 10 such as vanes, shrouds and baffles positioned radially inward from containment case 30 as well as components external or radially outward from case 30 such as bleed air pipe, electrical conduit, and/or lubrication lines, among other possible stationary components.
Bladed rotor 32 can be an integrally bladed rotor or a circumferential array of blades attached to a hub via a blade attachment such as a fir-tree or dovetail root. Each of the blades extends from a root to a tip in along a span direction and from a leading edge to a trailing edge in along a chord direction. The blade flanks include a suction side surface and a pressure side surface, each surface curved to form an airfoil profile along the chord direction from the leading edge to the trailing edge. Each bladed rotor 32 is operatively associated with a direction of rotation R about axis A of gas turbine engine 10. Compressor rotors, which impart work to the air flow, rotate in the direction of the pressure side surface. Turbine rotors, which extract work from the air flow, rotate in the direction of the suction side surface. Direction of rotation R may be described as clockwise or counterclockwise in the following disclosure, which refers to the direction of rotation as depicted in the figure.
Containment case 30 is formed by annular body 36 formed by multiple cylindrical and/or frustoconical sections, flanges, and other outer surface features and, in some examples, inner surface features. As depicted, containment case 30 includes upstream flange 38, frustoconical section 40, containment section 42, intermediate frustoconical section 44, cylindrical section 46, and downstream flange 48. In some examples, containment case 30 further includes frustoconical section 50. Annular body 36 is delimited by inner surface 36A and outer surface 36B, each extending axially from upstream flange 38 to downstream flange 48. Portions of inner surface 36A and outer surface 36B radially bound sections of annular body 36 discussed below. Further, containment case 30 includes reinforcement section 52 discussed in reference to
Upstream flange 38 and downstream flange 48 are radial flanges that extend outward from annular body 36. Circumferentially spaced clearance holes extend through axial faces of upstream flange 38 and downstream flange 48 and are spaced along a radius common to each flange for attaching containment case 30 to an adjacent component using fasteners (not shown).
Frustoconical sections 40, 44, and 50 have a frustoconical shape that increases or decreases the radial dimension of annular body 36 such that containment case 30 conforms to rotor geometry of gas turbine engine 10. Frustoconical section 40 extends axially from upstream flange 38 to containment section 42, decreasing the radial dimension of annular body 36 towards containment section 42. Frustoconical section 44 extends from a downstream end of containment section 42 towards cylindrical section 46, increasing the radial dimension of annular body 36. Frustoconical section 50 extends forward and radially inward from an upstream end of containment section 42.
Containment section 42 is a cylindrical region of annular body 36 positioned radially outward from and axially coincident with bladed rotor 32. An axial extent of containment section 42 encompasses an axial extent of bladed rotor 32. A casing thickness T of containment section 42 is defined by a radial distance between inner surface 36A and outer surface 36B of annular body 36 within containment section 42.
Containment case 30 can include outer surface feature 56, which forms a localized increase of casing thickness T. Outer surface feature 56 extends radially outward from outer surface 36B of annular body 36 that at least partially coincides axially with containment section 42. Example outer surface features 56 include, but are not limited to, a bracket, a lug, a boss, a protrusion, a rib segment, and a ring segment, among other possible outer surface features 56, each with or without threaded or clearance fastener holes. Outer surface features 56 can be used to mount or attach components of gas turbine engine 10 exterior to containment case 30. Example gas turbine engine components include bleed air pipe, electrical conduit, lubrication lines, modules containing electrical components of gas turbine engine 10, among other possible components.
During a blade out event or rotor burst event, blades and other fragments of bladed rotor 32 impact containment section 42 of containment case 30. The mass of the blade and/or rotor fragment(s), the rotational speed of bladed rotor 32, and the presence of one or more outer surface features 56 affect the impact energy imparted to containment case 30 during a blade or rotor failure. In order to minimize casing thickness T, containment case 30 includes reinforcement section 52 illustrated by
Reinforcement section 52 is a thickened region of containment case 30 that subtends a sector along a radially outer side of containment section 42. Reinforcement thickness TR is the radial distance between inner surface 36A and outer surface 36B within reinforcement section 52. Reinforcement thickness TR is greater than casing thickness T within portions of containment section 42 that are circumferentially adjacent reinforcement section 52.
The sector subtended by reinforcement section 52 is circumferentially limited by circumferential ends 52A and 52B. First circumferential end 52A rotationally precedes second circumferential end 52B relative to rotational direction R of bladed rotor 32. Outer surface feature 56 at least partial coincides with reinforcement section 52. In some examples, outer surface feature 56 is disposed entirely within reinforcement section 52. In further examples, outer surface feature 56 is disposed entirely within reinforcement section 52 and circumferentially coincides with second circumferential end 52B of reinforcement section 52. In yet another further example, an axial extent of reinforcement section 52 encompasses at least an axial extent of containment section 42. In other examples, reinforcement section 52 can have an axial extent that is more or less than an axial extent of containment section 42.
Reinforcement section 52 strengthens containment case 30 in a region proximate to outer surface feature 56 and allows reduction of case thickness T in a remainder of containment section 42. Accordingly, since reinforcement section 52 subtends a sector of containment section 42, the weight of containment case 30 can be reduced relative to an analogous containment case and predetermined impact energy.
The following are non-exclusive descriptions of possible embodiments of the present invention.
Containment Case with Outer Surface Reinforcement
A containment case according to an example embodiment of this disclosure, among other possible things includes an annular body and an outer surface feature. The annular body is limited by an outer surface and an inner surface. The annular body includes a containment section and a reinforcement section. The containment section has a casing thickness defined by a radial distance between the inner surface and the outer surface. The reinforcement section subtends a sector of the containment section that defines a reinforcement thickness between the inner surface and the outer surface that is greater than the casing thickness. The outer surface feature extends outward from the outer surface and at least partially coincides with the reinforcement section.
The containment case of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components.
A further embodiment of the foregoing containment case, wherein the outer surface feature can coincide with a circumferential end of the reinforcement section.
A further embodiment of any of the foregoing containment cases, wherein the outer surface feature can be entirely within the reinforcement section.
A further embodiment of any of the foregoing containment cases, wherein the inner surface of the containment section and the reinforcement section can be cylindrical.
A further embodiment of any of the foregoing containment cases, wherein the outer surface of reinforcement section can be radially outward from the outer surface of the containment section.
A further embodiment of any of the foregoing containment cases, wherein an axial extent of the reinforcement section can be at least equal to an axial extent of the cylindrical section.
A further embodiment of any of the foregoing containment cases, wherein the reinforcement section can include one or more ribs extending circumferentially along the containment section.
A further embodiment of any of the foregoing containment cases, wherein the reinforcement section can define an annular section.
A Gas Turbine Engine with a Containment Case and Outer Surface Reinforcement
A gas turbine engine according to an example embodiment of this disclosure, among other possible things includes a bladed rotor and a containment case. The bladed rotor is operatively associated with a direction of rotation about an axis of the gas turbine engine. The containment case includes an annular body and an outer surface feature. The annular body is limited by an outer surface and an inner surface. The annular body includes a containment section and a reinforcement section. The containment section has a casing thickness defined by a radial distance between the inner surface and the outer surface. The reinforcement section subtends a sector of the containment section that defines a reinforcement thickness between the inner surface and the outer surface that is greater than the casing thickness. The outer surface feature extends outward from the outer surface and at least partially coincides with the reinforcement section. The reinforcement section circumferentially precedes the outer surface feature relative to the direction of rotation.
The gas turbine engine of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components.
A further embodiment of the foregoing gas turbine engine, wherein the outer surface can coincide with a circumferential end of the reinforcement section.
A further embodiment of any of the foregoing gas turbine engines, wherein the outer surface can be entirely within the reinforcement section.
A further embodiment of any of the foregoing gas turbine engines, wherein the inner surface of the containment section and the reinforcement section can be cylindrical.
A further embodiment of any of the foregoing gas turbine engines, wherein the outer surface of reinforcement section can be radially outward from the outer surface of the containment section.
A further embodiment of any of the foregoing gas turbine engines, wherein an axial extent of the reinforcement section can be at least equal to an axial extent of the cylindrical section.
While the invention has been described with reference to an exemplary embodiment(s), it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment(s) disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
