# US 10,502,145 B2 · Integrated fuel and bleed system control architecture

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- Number: US 10,502,145 B2
- Document ID: US10502145B2
- Status: Granted
- Kind: B2
- Application number: 15/645,268
- Filed: 2017-07-10
- Published: 2019-01-10
- Granted: 2019-12-10
- Earliest claimed: 2017-07-10
- Assignees: Hamilton Sundstrand Corporation
- Applicants: Hamilton Sundstrand Corporation
- Inventors: Robert M. DeRoy; Adam Woods
- Web page: https://patentgrep.com/patent/US10502145B2

## CPC

- F02C 9/52: by bleeding or by-passing the working fluid
- F02C 6/08: the gas being bled from the gas-turbine compressor
- B64D 13/08: the air being heated or cooled
- B64D 15/04: Hot gas application
- B64D 31/06: actuated automatically
- B64D 2013/0618: {with arrangements for reducing or managing bleed air, using another air source, e.g. ram air}
- B64D 2013/0696: {with provisions for starting power plants}
- F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)}
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2220/50: for auxiliary power units (APU's)
- F05D 2260/20: Heat transfer, e.g. cooling
- F05D 2270/11: to prolong engine life
- F05D 2270/114: by limiting mechanical stresses
- F05D 2270/44: active, predictive, or anticipative
- F05D 2270/54: by electronic means, e.g. electronic tubes, transistors or IC's within an electronic circuit
- Y02T 50/50: On board measures aiming to increase energy efficiency
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A fuel and bleed controller is provided. The fuel and bleed controller includes a processor and a memory. The memory stores program instructions thereon. The program instructions are executable by the processor to cause the fuel and bleed controller to send status requests to systems of the aircraft. The systems comprise a bleed system and bleed user controllers. The program instructions are further executable by the processor to cause the fuel and bleed controller to receive status responses from the systems of the aircraft and determine fuel requirements based on the status responses in advance of operational needs by the systems of the aircraft. The program instructions are further executable by the processor to cause the fuel and bleed controller to control engines of the aircraft based on the fuel requirements.

## Claims

### Claim 1

A configuration for an aircraft comprising:
a fuel and bleed controller, the fuel and bleed controller comprising, a processor and a memory storing program instructions thereon,
a plurality of aircraft systems including:
a gas turbine engine controller;
a bleed system that uses bleed air to provide pneumatic power for internal cooling of the aircraft and to provide pneumatic power for one or more of: inert gas system (IGS), internal cooling of the engine, cross starting another engine on the aircraft, anti-icing for the engine, and anti-icing for the airframe; and
a plurality of bleed user controllers controlling operation of an environmental control system (ECS) and one or more of wing anti-ice (WAI) systems, the IGS and water supply systems;
the fuel and bleed controller is configured for bi-directional electronic communication with each of the plurality of aircraft systems;
the program instructions executable by the processor to cause the libel and bleed controller to:
send status updates requests to the plurality of aircraft systems;
receive status responses from to the plurality of aircraft systems;
determine fuel requirements based on the status responses in advance of operational needs by the plurality of aircraft systems;
the fuel requirements including predictive estimations of an amount of fuel needed by future power requests by the bleed system or the a plurality of bleed user controllers; and
control the engines of the aircraft based on the fuel requirements.

### Claim 2 (depends on 1)

The configuration of claim 1, wherein the status responses comprise operational information of the bleed system and the plurality of bleed user controllers.

### Claim 3 (depends on 1)

The configuration of claim 1, wherein the predictive estimations of the amount of fuel enable the fuel and bleed controller to control a consistent bleed pressure supply by the engine to avoid mechanical stress on the engine.

### Claim 4 (depends on 1)

The configuration of claim 1, wherein the fuel and bleed controller automatically receives environment inputs from the sensors of the aircraft.

### Claim 5 (depends on 4)

The configuration of claim 4, wherein the fuel requirements are determined based on the status responses and the environment inputs.

### Claim 6

A fuel and bleed control method comprising:
engaging in bi-directional electronic communications between a fuel and bleed controller of an aircraft and a plurality of aircraft systems, the bi-directional communications including the fuel and bleed controller requesting status updates, the plurality of on aircraft systems comprising:
a gas turbine engine controller;
a bleed system that uses bleed air to provide pneumatic power for internal cooling of the aircraft and to provide pneumatic power for one or more of: inert gas system (IGS), internal cooling of the engine, cross starting another engine on the aircraft, anti-icing for the engine, and anti-icing for the airframe; and
a plurality of bleed user controllers controlling operation of an environmental control system (ECS) and controlling operation of one or more of wing anti-ice (WAI) systems, the IGS and water supply systems;
receiving, by the fuel and bleed controller, status responses from the plurality of aircraft systems;
determining, by the fuel and bleed controller, fuel requirements based on the status responses in advance of operational needs by plurality of aircraft systems;
the fuel requirements including predictive estimations of an amount of fuel needed by future power requests by the bleed system or the plurality of bleed user controllers; and
controlling, by the fuel and bleed controller, one or more engines of the aircraft based on the fuel requirements.

### Claim 7 (depends on 6)

The fuel and bleed control method of claim 6, wherein the status responses comprise operational information of the bleed system and the plurality of bleed user controllers.

### Claim 8 (depends on 6)

The fuel and bleed control method of claim 6, wherein the predictive estimations of the amount of fuel enable the fuel and bleed controller to control a consistent bleed pressure supply by the engine to avoid mechanical stress on the engine.

### Claim 9 (depends on 6)

The fuel and bleed control method of claim 6, wherein the fuel and bleed controller automatically receives environment inputs from the sensors of the aircraft.

### Claim 10 (depends on 9)

The fuel and bleed control method of claim 9, wherein the fuel requirements are determined based on the status responses and the environment inputs.

### Claim 11 (depends on 1)

The configuration of claim 1, wherein:
the bleed system includes one or more of heat exchangers, manifold ducts, sensors, and valves, wherein the sensors are configured for communicating environmental inputs from the engine and/or aircraft.

### Claim 12 (depends on 6)

The method of claim 6, wherein:
the bleed system includes one or more of heat exchangers, manifold ducts, sensors, and valves, wherein the sensors are configured for communicating environmental inputs from the engine and/or aircraft.