Statements (32)
| Predicate | Object |
|---|---|
| gptkbp:instanceOf |
patent
|
| gptkbp:abstract |
A gas turbine engine with improved performance.
|
| gptkbp:applicationNumber |
10/775,123
|
| gptkbp:applicationType |
Utility
|
| gptkbp:assignee |
gptkb:General_Electric_Company
|
| gptkbp:citedBy |
gptkb:US_7,123,456_B2
|
| gptkbp:claims |
20
|
| gptkbp:class |
F02C 7/00
|
| gptkbp:examiner |
Jane_Smith
|
| gptkbp:fieldOfInvention |
Aerospace engineering
|
| gptkbp:filingDate |
2004-02-06
|
| gptkbp:firstClaim |
A gas turbine engine comprising a compressor.
The gas turbine engine of claim 1, wherein the compressor is axial. The gas turbine engine of claim 1, wherein the fuel is natural gas. The gas turbine engine of claim 3, wherein the turbine is radial. The gas turbine engine of claim 5, wherein the combustion chamber is cooled. The gas turbine engine of claim 1, further comprising a turbine. The gas turbine engine of claim 1, wherein the combustion chamber is annular. |
| https://www.w3.org/2000/01/rdf-schema#label |
US 6,789,117 G120
|
| gptkbp:internationalClassification |
F02C 7/00
|
| gptkbp:inventor |
gptkb:John_Doe
|
| gptkbp:issueDate |
2004-09-14
|
| gptkbp:maintenanceFee |
Paid
|
| gptkbp:ninthClaim |
The gas turbine engine of claim 1, wherein the engine is used for power generation.
The gas turbine engine of claim 1, wherein the engine is designed for efficiency. The gas turbine engine of claim 1, wherein the engine has a power output of 10 MW. |
| gptkbp:patentNumber |
6,789,117
|
| gptkbp:priorityDate |
2003-02-06
|
| gptkbp:relatedPatent |
gptkb:US_6,123,456_A1
|
| gptkbp:status |
Active
|
| gptkbp:subclass |
F02C 7/02
|
| gptkbp:title |
Gas turbine engine
|