Abstract: A method for suppressing the expression of a selected apoptosis-related gene in a cell the method comprising introducing into the cell a molecule comprising (1) a nucleic acid binding portion which binds to a site at or associated with the selected gene which site is present in a genome and (2) a modifying portion, wherein the nucleic acid binding portion comprises an oligonucleotide or oligonucleotide mimic or analogue, and wherein the repressor portion comprises a polypeptide or peptidomimetic. Molecules for use in the methods of the invention are provided. The repressor or modifying portion may be a portion of a histone deacetylase or DNA methylase or polypeptide capable of recruiting a histone deacetylase or DNA methylase. The nucleic acid binding portion may be a triplex forming oligonucleotide (TFO). The apoptosis-related gene may be Bcl-2.

Abstract: A method for suppressing the expression of a selected gene in a cell the method comprising introducing into the cell a molecule comprising (1) a nucleic acid binding portion which binds to a site or associated with the selected gene which site is present in a genome and (2) an expression repressor portion, wherein the nucleic acid binding portion comprises an oligonucleotide or oligonucleotide mimic or analogue, and wherein the repressor portion comprises a polypeptide or peptidomimetic. Molecules for use in the methods of the invention are provided. The repressor may be a portion of a histone deacetylase or DNA methylase or polypeptide capable of recruiting a histone deacetylase or DNA methylase.

Abstract: An aircraft gas turbine has a barrier air flow produced by the fan or a low-pressure compressor which passes continuously through the compressor bearing chamber, while the turbine bearing chamber is supplied with barrier air by the high-pressure compressor. The barrier air flow drawn from the turbine bearing chamber passes into an ejector which is also connected to the compressor bearing chamber so that, when the pressure is insufficient, the barrier air flow is drawn-off by the ejector.

Abstract: In a blade cooling system for a turbine of a gas turbine engine each blade root is provided with individual pitot receivers which collect a portion of a cooling fluid flow supplied from an annular array of pre-swirl nozzles, which have a circumferentially continuous outlet flow area, and direct said flow into a portion only of the interior of the blade, preferably adjacent the leading edge.

Abstract: Thermal matching of compounds in a gas turbine engine is achieved by providing the component with the highest rate of thermal expansion with an insulating sheet which is dimpled to contact the surface of the component at discrete spots leaving air spaces in between. The sheet is attached to the component by spot welding at a pre-determined number of areas to provide the necessary heat conducting paths between the insulation and the component to enable the expansion of the component to be matched with that of another component. Seal clearances can be reduced by matching the expansions of seal carrying components in this way.