Descent operation for an aircraft parallel hybrid gas turbine electric propulsion system

Patent metadata

Field	Value
Publication number	US-11428170-B2
Application number	US-201615200149-A
Country	US
Kind code	B2
Filing date	Jul 1, 2016
Priority date	Jul 1, 2016
Publication date	Aug 30, 2022
Grant date	Aug 30, 2022

Abstract

A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.

First claim

The invention claimed is:

1. An aircraft including a gas turbine engine comprising:
a core including a compressor section having a first compressor and a second compressor, a turbine section having a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section;
the first compressor is connected to the first turbine via a first shaft;
the second compressor is connected to the second turbine via a second shaft;
a motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft;
wherein the gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation;
a controller configured to control the mode of operation of the at least one gas turbine engine; and
wherein the at least one additional mode of operation includes a cruise mode of operation and a geometry of the gas turbine engine is physically sized such that a turbine inlet temperature of the second turbine is at a maximum temperature for the top of climb mode of operations while said engine is in said cruise mode of operation, and wherein the maximum turbine inlet temperature corresponds to a maximum thrust output of the core and the maximum thrust output of the core is less than an aircraft thrust requirement on the gas turbine engine in at least one of the takeoff mode of operations and the top of climb mode of operations.

2. The aircraft of claim 1 , wherein the at least one additional mode of operation includes a descent mode of operation.

3. The aircraft of claim 2 , wherein an air pressure from at least one compressor bleed is replaced by air pressure from an electric compressor during the descent mode of operation.

4. The aircraft of claim 3 , wherein the electric compressor is electrically coupled to an energy storage system, and wherein the energy storage system stores energy generated by said motor during the at least one additional mode of operation.

5. The aircraft of claim 2 , further comprising the controller being configured to control said engine such that a fan windmills during said descent mode of operation, wherein the fan is interconnected with the first shaft via a gear system such that rotation of the fan is translated to the first shaft.

6. The aircraft of claim 2 , wherein the motor is configured as a motor during the descent mode of operation, and wherein an energy storage device provides operational power to the motor during the descent mode of operation.

7. The aircraft of claim 6 , wherein the controller is configured to cause the motor to generate an amount of power equal to an amount of power required to overcome the engine drag during said descent mode of operation.

8. The aircraft of claim 2 , wherein the controller is configured to prevent the core from operating during the descent mode of operation.

9. The aircraft of claim 1 , further comprising a fan section forward of the first compressor, the fan section including a fan connected to the first shaft via a geared architecture.

10. The aircraft of claim 1 , wherein the at least one additional mode of operation includes a cruise mode of operation and a flow rate through the gas turbine engine is configured to be controlled by a controller such that a turbine inlet temperature of the second turbine is at a maximum while said engine is in said cruise mode of operation.

11. An aircraft including a gas turbine engine comprising:
a core including a compressor section having a first compressor and a second compressor, a turbine section having a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section;
the first compressor is connected to the first turbine via a first shaft;
the second compressor is connected to the second turbine via a second shaft;
a motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft;
wherein the gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation;
a controller configured to control the mode of operation of the gas turbine engine; and
wherein the at least one additional mode of operation includes a cruise mode of operation and a flow rate through the gas turbine engine is configured to be controlled by a controller such that a turbine inlet temperature of the second turbine is at a maximum while said engine is in said cruise mode of operation, and wherein the maximum turbine inlet temperature corresponds to a maximum thrust output of the core and the maximum thrust output of the core is less than an aircraft thrust requirement of the gas turbine engine in at least one of the takeoff mode of operations and the top of climb mode of operations.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Lents Charles E
• Hardin Larry W
• Rheaume Jonathan
• Staubach Joseph B

Classifications

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• F02C7/36 Primary

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• B64D31/06

  actuated automatically · CPC title

• F01D15/10 Primary

  Adaptations for driving, or combinations with, electric generators · CPC title