Rolls-Royce Patente

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A gas turbine engine (10) for an aircraft (1), comprising: a combustor (16); a fuel-oil heat exchanger (1004; 1006; 1204; 1206; 1404; 1406; 1704; 1706) arranged to receive fuel from a fuel tank (50) on board the aircraft (1) and transfer heat from the oil to the fuel; a fuel return line (1011; 1211; 1411b; 1711b) arranged to return at least some fuel that has passed through the heat exchanger (1004; 1006; 1204; 1206; 1404; 1406; 1704; 1706) to the fuel tank (50); and a modulator valve (1010; 1210; 1410; 1710) arranged to modulate the flow of fuel along the fuel return line (1011; 1211; 1411b; 1711b) such that a ratio of a temperature, in Kelvin, of fuel in the fuel tank (50) to a temperature, in Kelvin, of fuel being delivered to the combustor (16) is less than 0.56. Methods (2000) of operating a gas turbine engine (10) are also disclosed.

A gas turbine engine (10) for an aircraft comprises an engine core (11) comprising a turbine (19), a combustor (16), a compressor (14), and a core shaft (26) connecting the turbine to the compressor. The engine comprises a fan (23) located upstream of the engine core and arranged to be driven by the core shaft. The engine comprises a nacelle (21) surrounding the fan and the engine core and defining a bypass duct (22) located radially outside of the engine core, where the bypass ratio, defined as the ratio of the mass flow rate of the flow through the bypass duct to the mass flow rate of the flow through the core at cruise conditions, is at least 4. The engine comprises an engine heat management system (1700) and an actuator (1704) configured to actuate at least one valve (1704a) within that system. The engine comprises a fuel supply system (152) arranged to supply fuel to fueldraulically drive the actuator. The actuator is configured to actuate said valve so as to enable non-binary position adjustment between an open valve position and a closed valve position.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Electrical power systems for distributing electrical power in arrangements comprising one or more gas turbine engines 101 are described. One such electrical power system comprises: one or more rotary electric machines 111-113, each mechanically coupled to a gas turbine engine spool; a set of converter circuits 203 connected to the one or more rotary electric machines 111-113 for conversion between alternating current (ac) and direct current (dc), wherein the one or more rotary electric machines 111-113 and the set of converter circuits 203 are arranged to output a number R ≥ 2 of dc power channels 206-209, each dc power channel 206-209 having a respective index r = (1, ..., R); and a group of N dc load channels 400-1200 connected to the R dc power channels 206-209 by a switching arrangement 410-1210, wherein each dc load channel 400-1200 has a respective index n = (1, ..., N) and R < N ≤ 2R. The switching arrangement 410-1210 is operable to connect the r-th power channel to the n-th load channel according to the relationship: r n = { 1 , n = 1 n 2 and n 2 + 1 , 1 < n < N and n = 0 mod 2 n − 1 2 and n + 1 2 , 1 < n < N and n = 1 mod 2 R , n = N . <img class="EMIRef" id="11d533c3-f48a-4207-a3ab-131d04c4fd5b-ia01" />

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

In one example, a method for forming a coating system including an environmental barrier coating (EBC) and abradable coating on a substrate. The method may include depositing the EBC on a ceramic or ceramic matric composite (CMC) substrate to form an as-deposited EBC; heat treating the as-deposited EBC following the deposition of the as-deposited EBC on the substrate to form a heat treated EBC; and subsequently depositing an abradable coating on the heat treated EBC to form an as-deposited abradable coating. The as-deposited abradable coating may be heat treated to form a heat treated abradable coating.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

There is provided a blower system 400 for providing air to an airframe system 450, comprising a rotor 410 configured to be mechanically coupled to a spool 440 of a gas turbine engine 10, wherein the rotor 410 is configured to: in a blower mode, be driven to rotate by the spool 440 to discharge air to an airframe discharge port 426 for supply to an airframe system 450; and, in an engine drive mode, receive air from an external air source 470 via an impingement port 424 that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool 440 to.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …