Twin centrifugal single spool engine

Patent metadata

Field	Value
Publication number	US-10364041-B2
Application number	US-201615218915-A
Country	US
Kind code	B2
Filing date	Jul 25, 2016
Priority date	Jul 25, 2016
Publication date	Jul 30, 2019
Grant date	Jul 30, 2019

Abstract

An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.

First claim

What is claimed is:

1. An auxiliary power unit, comprising:
a twin centrifugal compressor comprising:
a forward centrifugal compressor having a first aft end and a first forward end;
an aft centrifugal compressor disposed aft of the forward centrifugal compressor, the aft centrifugal compressor having a second aft end and a second forward end;
a first airflow path at an input of the twin centrifugal compressor;
a second airflow path defined by the forward centrifugal compressor, wherein the second airflow path is directed forward from the first aft end toward the first forward end;
a third airflow path defined by the aft centrifugal compressor, wherein the third airflow path is directed aft from the second forward end toward the second aft end;
a manifold disposed aft of the forward centrifugal compressor and the aft centrifugal compressor, the manifold defining a fourth airflow path, wherein the fourth airflow path is comprised of a mix of the second airflow path and the third airflow path, and wherein the fourth airflow path is co-axial with the second airflow path and the third airflow path; and

a combustor comprising an annular reverse flow combustor, wherein the fourth airflow path is further defined by the annular reverse flow combustor.

2. The auxiliary power unit of claim 1 , further including a blade, wherein the blade comprises silicon nitride.

3. The auxiliary power unit of claim 1 , wherein the second airflow path and the third airflow path are co-axial within the twin centrifugal compressor.

4. The auxiliary power unit of claim 1 , wherein a second pressure of the second airflow path is substantially the same as a third pressure of the third airflow path.

5. The auxiliary power unit of claim 1 , wherein a pressure ratio of at least one of the second airflow path or the third airflow path to the first airflow path is 7:1 or greater.

6. An auxiliary power unit, comprising:
a forward centrifugal compressor having a first aft end and a first forward end;
an aft centrifugal compressor disposed aft of the forward centrifugal compressor, the aft centrifugal compressor having a second aft end and a second forward end;
a second airflow path defined by the forward centrifugal compressor, wherein the second airflow path is directed forward from the first aft end toward the first forward end;
a third airflow path defined by the aft centrifugal compressor, wherein the third airflow path is directed aft from the second forward end toward the second aft end;
an annular reverse flow combustor disposed aft of the aft centrifugal compressor; and
a turbine disposed radially inward of the annular reverse flow combustor and aft of the aft centrifugal compressor.

7. The auxiliary power unit of claim 6 , wherein the forward centrifugal compressor further comprises a blade.

8. The auxiliary power unit of claim 7 , wherein the blade includes silicon nitride.

9. The auxiliary power unit of claim 7 , wherein a forward diameter of the forward centrifugal compressor is smaller than an aft diameter of the aft centrifugal compressor.

10. The auxiliary power unit of claim 7 , further comprising a first airflow path defined between the forward centrifugal compressor and the aft centrifugal compressor, wherein the second airflow path and the third airflow path being split from the first airflow path.

11. The auxiliary power unit of claim 10 , wherein the second airflow path and the third-airflow path are co-axial.

12. The auxiliary power unit of claim 11 , wherein a second pressure of the second airflow path is substantially the same as a third pressure of the third airflow path.

13. The auxiliary power unit of claim 11 , further comprising a manifold, wherein the manifold defines a fourth airflow path, wherein the fourth airflow path is comprised of a mix of the second airflow path and the third airflow path.

14. An auxiliary power unit, comprising:
a twin centrifugal compressor including a first blade;
an engine case structure, wherein the engine case structure and the twin centrifugal compressor define a first airflow path, wherein the twin centrifugal compressor defines a second airflow path and a third airflow path from the first airflow path, wherein the second airflow path is directed forward and the third airflow path is directed aft;
a fourth airflow path comprising a mix of the second airflow path and the third airflow path, the fourth airflow path being co-axial with the second airflow path and the third airflow path;
a combustor comprising an annular reverse flow combustor, wherein the annular reverse flow combustor further defines the fourth airflow path;
a turbine disposed aft of the twin centrifugal compressor and radially inward of the combustor, the turbine including a second blade.

15. The auxiliary power unit of claim 14 , wherein the first blade comprises a first material and the second blade comprises a second material and wherein the first material is the same as the second material.

16. The auxiliary power unit of claim 14 , wherein the first blade comprises silicon nitride.

17. The auxiliary power unit of claim 14 , wherein a diameter of the turbine is between 10 centimeters (3.94 inches) to 18 centimeters (7.09 inches).

Assignees

• United Technologies Corp

Inventors

• Kupratis Daniel Bernard
• Utay Arthur W
• Kashyap Tania Bhatia
• Slavens Thomas N
• Rugg Kevin L
• Zelesky Mark F
• Merry Brian D
• Suciu Gabriel L

Classifications

• F04D17/105

  with double suction · CPC title

• F02C3/145

  the combustion chamber being in the reverse flow-type · CPC title

• F02C3/08

  the compressor comprising at least one radial stage (F02C3/10 takes precedence) · CPC title

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title