Multistage turbocharging system for providing constant original critical altitude pressure input to high pressure stage turbocharger

Patent metadata

Field	Value
Publication number	US-10940954-B2
Application number	US-201615757828-A
Country	US
Kind code	B2
Filing date	Aug 25, 2016
Priority date	Sep 17, 2015
Publication date	Mar 9, 2021
Grant date	Mar 9, 2021

Abstract

An aircraft engine system configured with a high pressure stage turbocharger assembly and a supplemental stage turbocharger assembly disposed in series with respect to said high pressure stage turbocharger, wherein the supplemental stage turbocharger assembly provides a compressor unit of the high pressure stage turbocharger with substantially constant critical altitude pressure input.

First claim

The invention claimed is:

1. A method of retrofitting an aircraft engine system, the method comprising:
receiving the aircraft engine system including an initially fitted high pressure stage turbocharger assembly including a high pressure stage wastegate and a turbocharger control unit configured for controlling pressure input to an aircraft engine by controlling an extent to which the high pressure stage wastegate opens and closes; and
retrofitting the aircraft engine system by at least adding at least one retrofit supplemental stage turbocharger assembly to the aircraft engine in series with respect to the high pressure stage turbocharger of the initially fitted high pressure stage turbocharger assembly;
wherein the at least one retrofit supplemental stage turbocharger assembly including a supplemental wastegate and a supplemental turbocharger control unit separate and distinct from the turbocharger control unit;
wherein the supplemental turbocharger control unit is configured for controlling pressure input to the initially fitted high pressure stage turbocharger assembly by controlling an extent to which the supplemental wastegate opens and closes, so that the at least one retrofit supplemental stage turbocharger assembly provides a compressor unit of the initially fitted high pressure stage turbocharger assembly with substantially constant original critical altitude pressure input when the aircraft engine system is located above an original critical altitude and below a new critical altitude.

2. The method of claim 1 wherein adding at least one retrofit supplemental stage turbocharger assembly to the aircraft engine in series with respect to the high pressure stage turbocharger of the initially fitted high pressure stage turbocharger assembly includes attaching the at least one retrofit supplemental stage turbocharger assembly to the aircraft engine in series with respect to the high pressure stage turbocharger of the initially fitted high pressure stage turbocharger assembly.

3. The method of claim 1 wherein after the retrofitting, the turbocharger control unit of the high pressure stage turbocharger assembly is configured to be operated in a closed-loop system within the high pressure stage turbocharger assembly.

4. The method of claim 1 wherein after the retrofitting, the turbocharger control unit substantially does not transfer or receive control signals from the at least one retrofit supplemental stage turbocharger assembly.

5. The method of claim 1 wherein after the retrofitting, the at least one retrofit supplemental stage turbocharger assembly substantially does not transfer or receive control signals from the high pressure stage turbocharger assembly.

Assignees

• Israel Aerospace Ind Ltd

Inventors

• Fass Yehuda
• Feldman Jacob

Classifications

• F02B61/04

  for driving propellers · CPC title

• B64D27/04 Primary

  of piston type · CPC title

• F02B37/18

  by bypassing exhaust {from the inlet to the outlet of turbine or to the atmosphere} · CPC title

• F02K3/075

  controlling flow ratio between flows · CPC title

• F02D41/0007

  for control of turbo-charged or super-charged engines (control of the pumps per se F02B37/12) · CPC title