GAS TURBINE ENGINE HAVING ENERGY DISSIPATING GAP AND CONTAINMENT LAYER
A gas turbine engine includes a containment ring to contain liberated compressor and turbine blades and blade fragments within a core assembly. The combination of a containment gap between the core case and the containment ring and a containment layer disposed in the gap helps dissipate the energy generated by loose body impacts on the core assembly. The containment layer deforms, deflects, and/or redirects the impact energy acting in a radial direction, thereby to improve containment.
1 . A gas turbine engine disposed along a longitudinal engine axis, the gas turbine engine comprising:
a fan assembly;
a core assembly coupled to the fan assembly, the core assembly including:
a compressor section including at least one compressor having a plurality of compressor blades;
a turbine section including at least one turbine having a plurality of turbine blades;
a combustor section disposed between the compressor section and the turbine section;
a core case surrounding the compressor section, the turbine section, and the combustor section, and defining a core case first surface;
a blade containment ring surrounding at least one of the compressor section and the turbine section and defining a containment ring first surface spaced from and oriented towards the core case first surface to define a containment gap therebetween; and
a containment layer disposed in the containment gap and configured to dissipate energy from radially projecting impacts.
2 . The gas turbine engine of claim 1 , in which the core case first surface comprises a core case inner surface and the containment ring first surface comprises a containment ring outer surface, so that the containment ring is disposed nearer to the core longitudinal axis than the core case.
3 . The gas turbine engine of claim 1 , in which the core case first surface comprises a core case outer surface and the containment ring first surface comprises a containment ring inner surface, so that the containment ring is disposed farther from the core longitudinal axis than the core case.
4 . The gas turbine engine of claim 1 , in which the containment ring is directly coupled to the core case.
5 . The gas turbine engine of claim 1 , in which the containment layer comprises a plating layer disposed on the containment ring first surface.
6 . The gas turbine engine of claim 5 , in which the plating layer is formed of a malleable metal or malleable metal alloy.
7 . The gas turbine engine of claim 1 , in which the containment layer comprises a temperature-responsive shape memory layer having a retracted state at a relatively low temperature and an expanded state at a relatively high temperature.
8 . The gas turbine engine of claim 1 , in which the containment layer comprises a matrix composite layer.
9 . The gas turbine engine of claim 8 , in which the matrix composite layer comprises a matrix composite material selected from a group of matrix composite materials consisting of a metal matrix composite, a ceramic matrix composite, a metal honeycomb composite, and an organic matrix composite.
10 . The gas turbine engine of claim 1 , in which the containment layer comprises a filler layer configured to substantially entirely fill the containment gap.
11 . The gas turbine engine of claim 10 , in which the filler layer comprises a filler material selected from a group of filler materials consisting of a ceramic material and a non-Newtonian fluid.
12 . The gas turbine engine of claim 1 , in which the containment layer comprises a weave layer having woven metal fibers.
13 . The gas turbine engine of claim 1 , in which the containment layer comprises a resilient layer.
14 . A gas turbine engine disposed along a longitudinal engine axis, the gas turbine engine comprising:
a fan assembly;
a core assembly coupled to the fan assembly, the core assembly including:
a compressor section;
a turbine section;
a combustor section disposed between the compressor section and the turbine section;
a core case surrounding the compressor section, the turbine section, and the combustor section, and defining a core case first surface;
a blade containment ring surrounding at least one of the compressor section and the turbine section and defining a containment ring first surface spaced from and oriented towards the core case first surface to define a containment gap therebetween; and
a containment layer disposed in the containment gap and configured to dissipate energy from radially projecting impacts, the containment layer including a plating layer disposed on the containment ring first surface.
15 . The gas turbine engine of claim 14 , in which the plating layer is formed of a malleable metal or malleable metal alloy.
16 . The gas turbine engine of claim 14 , in which the plating layer is formed of copper.
17 . The gas turbine engine of claim 14 , in which the plating layer is formed on the containment ring first surface by plating, coating, or transient liquid phase bonding.
18 . A core assembly in a gas turbine engine, the core assembly comprising:
a compressor section;
a turbine section;
a core case surrounding the compressor section and the turbine section and defining a core case first surface;
a blade containment ring surrounding at least one of the compressor section and the turbine section and defining a containment ring first surface spaced from and oriented towards the core case first surface to define a containment gap therebetween; and
a containment layer disposed in the containment gap and configured to dissipate energy from radially projecting impacts, the containment layer including a weave layer having woven metal fibers.
19 . The core assembly of claim 18 , in which the weave layer comprises a first set of fibers oriented along a first fiber direction and a second set of fibers oriented along a second fiber direction, and in which the second fiber direction forms a fiber angle θ relative to the first fiber direction.
20 . The core assembly of claim 18 , in which the containment layer further comprises a second weave layer of woven metal fibers.