1. A non-aqueous electrolyte comprising:
an electrolyte salt;
an organic solvent; and
an additive for a non-aqueous electrolyte,
wherein the additive for a non-aqueous electrolyte is a compound represented by the following Formula 1 and having a double bond and at least two cyano groups, wherein the two of the at least two cyano groups are in a trans-formation to the double bond,
wherein the electrolyte salt is formed of a combination of (i) a cation selected from the group consisting of Li+, Na+ and K+; and (ii) an anion selected from the group consisting of PF6\u2212, BF4\u2212, Cl\u2212, Br\u2212, I\u2212, ClO4\u2212, AsF6\u2212; CH3CO2\u2212, CF3SO3\u2212, N(CF3SO2)2\u2212 and C(CF2SO2)3\u2212,
wherein the organic solvent is at least one solvent selected from the group consisting of cyclic carbonates, linear carbonates, lactones, ethers, esters, sulfoxides, acetonitriles, lactams, ketones and halogen derivatives thereof:
wherein the compound represented by the Formula 1 is 1,1,4,4-tetracyanobutene.
2. The non-aqueous electrolyte as claimed in claim 1, wherein the additive is used in an amount of 0.01-10 wt % in the non-aqueous electrolyte.
3. The non-aqueous electrolyte as claimed in claim 1, wherein the anion is BF4\u2212.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A rotor assembly for a gas turbine engine, the rotor assembly comprising:
a disc supporting a plurality of radially extending blades,
the blades defining passages between their circumferentially-facing surfaces and each of these passages having an annulus filler assembly; and
the annulus filler assembly comprising at least two bodies and a brace,
each of the bodies being mounted to one of adjacent said blades and the brace occupying a position centrally of the at least two bodies,
each of the bodies and the brace interacting with one another to form an airwash surface,
the interaction of the brace with at least one said body forming a floating and moveable seal,
the seal having a lip arranged to overlap a co-operating feature, and
the feature having a radially outer opposing wall and a radially inner opposing wall to define a slot by way of a radial gap between the opposing walls and the lip being located centrally therebetween so as to be within the slot and movable relative to the opposing walls.
2. A rotor assembly for a gas turbine engine as claimed in claim 1, wherein the brace is mounted to the disc.
3. A rotor assembly for a gas turbine engine as claimed in claim 1, wherein the lip comprises at least one inward step in a radial direction of the disc and the at least one inward step forms at least one ledge on the lip.
4. A rotor assembly for a gas turbine engine as claimed in claim 1, wherein the radially inner opposing wall has a first captive ridge and the lip comprises a bulbous curve at the radially inner extremity of the lip.
5. A rotor assembly for a gas turbine engine, the rotor assembly comprising:
a disc supporting a plurality of radially extending blades,
the blades defining passages between their circumferentially-facing surfaces and each of these passages having an annulus filler assembly; and
the annulus filler assembly comprising at least two bodies, each of which comprises a hollow box-section constituted by walls surrounding an interior opening, and a brace,
each of the bodies being mounted to one of adjacent said blades and the brace occupying a position centrally of the at least two bodies,
each of the bodies and the brace interacting with one another to form an airwash surface,
the interaction of the brace with at least one said body forming a floating and moveable seal,
the seal having a lip arranged to overlap a co-operating feature, and
the feature having a radially outer opposing wall and a radially inner opposing wall to define a slot by way of a radial gap between the opposing walls and the lip being located centrally therebetween so as to be within the slot and movable relative to the opposing walls.
6. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip is a wedge tapering to an edge at the lip extremity.
7. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip comprises at least one inward step in a radial direction of the disc and the at least one inward step forms at least one ledge on the lip.
8. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip comprises a plurality of inward steps in a radial direction of the disc forming a plurality of ledges.
9. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the radially inner opposing wall has a first captive ridge.
10. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the radially outer opposing wall has a second captive ridge.
11. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip comprises a bulbous curve at the radially inner extremity of the lip.
12. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip comprises at least one knuckle at the extremity of the lip.
13. A rotor assembly for a gas turbine engine as claimed in claim 7, wherein the at least one ledge comprises a fabric section.
14. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the brace has a retention feature and is mounted to the disc by way of a complementary retention feature defined by the disc and located between the respective adjacent said blades.
15. A rotor assembly for a gas turbine engine, the rotor assembly comprising:
a disc supporting a plurality of radially extending blades,
the blades defining passages between their circumferentially-facing surfaces and each of these passages having an annulus filler assembly that extends from a trailing edge to a leading edge of each of the blades defining the each passage; and
the annulus filler assembly comprising at least two bodies and a brace,
each of the bodies being mounted to one of adjacent said blades and the brace occupying a position centrally of the at least two bodies,
each of the bodies and the brace interacting with one another to form an airwash surface,
the interaction of the brace with at least one said body forming floating and moveable seal,
the seal having a lip arranged to overlap a co-operating feature,
the feature having a radially outer opposing wall and a radially inner opposing wall to define a slot by way of a radial gab between the opposing walls and the lip being located centrally therebetween so as to be within the slot and movable relative to the opposing walls, and
the rotor assembly being a fan assembly and the blades being fan blades.